Wind measurement equipment and unmanned aerial vehicle

Abstract

The invention provides wind measuring equipment and an unmanned aerial vehicle, the wind measuring equipment is used for being carried on the unmanned aerial vehicle, the wind measuring equipment comprises a wind measuring instrument, a self-stabilizing device and a controller, the self-stabilizing device is used for being installed on the top of the unmanned aerial vehicle, and the self-stabilizing device comprises a first rotating part and a second rotating part; the rotating axis of the first rotating part and the rotating axis of the second rotating part extend horizontally and are perpendicular to each other; the first rotating part is connected to the second rotating part, the wind meter is installed on the first rotating part, and the controller is used for controlling rotation of the first rotating part and the second rotating part. The wind measuring equipment can follow the unmanned aerial vehicle to flexibly measure wind.

Description

Technical Field

[0001] The present invention relates to the technical field of wind measurement, and particularly to a wind measurement device and a drone. Background Art

[0002] In engineering practice, there is often a need for wind measurement, that is, to detect parameters such as wind speed and wind direction. For example, for a wind turbine generator, wind measurement is required during its design, manufacture, operation, etc. Generally, the method adopted is to fix an anemometer on infrastructure such as a tower for measurement. The measurement position is fixed, and the measurement is not convenient. Summary of the Invention

[0003] The purpose of the present application is to provide a wind measurement device and a drone, which can perform wind measurement more flexibly following the drone.

[0004] The wind measurement device provided by the present application is used to be carried on a drone. The wind measurement device includes an anemometer, a self-stabilizing device, and a controller. The self-stabilizing device is used to be installed on the top of the drone. The self-stabilizing device includes a first rotating member and a second rotating member. The rotation axes of the first rotating member and the second rotating member extend horizontally and are perpendicular to each other. The first rotating member is connected to the second rotating member. The anemometer is installed on the first rotating member. The controller is used to control the rotation of the first rotating member and the second rotating member.

[0005] Optionally, the wind measurement device includes an equipment cabin. The self-stabilizing device further includes a third rotating member. The controller also controls the rotation of the third rotating member. The second rotating member is connected to the third rotating member. The rotation axis of the third rotating member extends vertically. The third rotating member is arranged inside the equipment cabin.

[0006] Optionally, a first support assembly is arranged inside the equipment cabin. The first support assembly includes a first side plate and a second side plate. The self-stabilizing device includes a base. The third rotating member is installed on the base. The base is clamped between the first side plate and the second side plate.

[0007] Optionally, the first support assembly further includes a support plate. The support plate connects the first side plate and the second side plate. The support plate divides the space between the first side plate and the second side plate into an upper cavity and a lower cavity. The base is located in the upper cavity. The wind measurement device further includes a power supply for supplying power to the self-stabilizing device. The power supply is arranged in the lower cavity.

[0008] Optionally, the controller is arranged on the side of the first side plate away from the second side plate.

[0009] Optionally, a data acquisition device is further included, and the data acquisition device is arranged on a side of the second side plate away from the first side plate, and the data acquisition device is connected to the wind meter signal.

[0010] Optionally, a side wall of the equipment compartment is provided with an external signal interface, and the signal interface is connected to the data acquisition instrument signal.

[0011] Optionally, the first rotating component, the second rotating component and the third rotating component are all rotating motors, and the housings of the rotating motors are made of alloy materials.

[0012] Optionally, the wind measuring equipment includes a second support assembly, the second support assembly includes a vertically arranged first support rod and a horizontally arranged second support rod; the self-stabilizing device is installed at one end of the first support rod, the other end of the first support rod is connected to the second support rod, and the second support rod is used to be installed on the top of the drone.

[0013] Optionally, a data acquisition instrument is provided in the equipment cabin, and the data acquisition instrument is located below the first support rod. The first support rod has an inner cavity, and the data line of the anemometer passes through the inner cavity of the first support rod and is connected to the data acquisition instrument signal.

[0014] Optionally, a shock-absorbing sponge rubber is arranged between the anemometer and the first rotating component.

[0015] Optionally, the wind measuring device includes a mounting bracket for fixing the equipment cabin to the drone, and the height of the front side of the mounting bracket is higher than the height of the rear side thereof.

[0016] The present application also provides an unmanned aerial vehicle, comprising a body and wings, wherein the top of the body is equipped with any of the above-mentioned wind measuring devices.

[0017] The wind measuring device in the application can adjust the posture of the anemometer through a self-stabilizing device, so that the anemometer is not affected by the wind and the tilt angle of the drone, and can maintain a relatively stable posture to measure the wind speed. In addition, the anemometer can be installed on the top of the drone through the equipment cabin, so that it will not be affected by the airflow generated by the wings of the drone during flight, thereby improving the accuracy of the anemometer detection data.

[0018] The wind measuring equipment in this application can adjust the posture of the anemometer through a self-stabilizing device, so that the anemometer is as unaffected as possible by the wind and the tilt angle of the drone, so as to maintain a relatively stable posture for measuring wind speed, thereby being able to flexibly measure wind by following the drone.

[0019] The drone in the application is equipped with wind measuring equipment, which can increase the reliability of using drones to measure wind speed, wind direction and other data, thereby eliminating the need to use expensive fixed iron towers, deploy laser radars and other wind measurement methods. Moreover, using drones, accurate real-time measurements of wind speed and wind direction data can be quickly obtained at any time, in any desired geographical location (such as mountains, oceans, uninhabited deserts, etc.), and at any height. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of a wind measuring device mounted on a drone in an embodiment of the present application;

[0021] Figure 2 for Figure 1 Schematic diagram of the wind measurement equipment installed on the top of the drone;

[0022] Figure 3 for Figure 2 Schematic diagram of the wind measurement equipment;

[0023] Figure 4 This is a schematic diagram of the three-dimensional structure of the wind measuring device mounted on a drone in an embodiment of the present application;

[0024] Figure 5 for Figure 4 A magnified view of the location of the wind measuring equipment;

[0025] Figure 6 for Figure 5 Schematic diagram of the self-stabilizing device;

[0026] Figure 7 This is a structural schematic diagram of a wind measuring device in the second embodiment of the present application;

[0027] Figure 8 for Figure 7 Schematic diagram of the wind measurement equipment from another perspective.

[0028] The reference numerals in the above drawings are described as follows:

[0029] 100-UAV; 101-wing; 102-body;

[0030] 200- Wind measuring equipment;

[0031] 1-equipment compartment; 1a-opening; 11-battery compartment cover; 12-top cover; 2-data acquisition instrument; 3-controller; 4-first support assembly; 41-first side plate; 411-connection hole; 42-second side plate; 43-support plate; 4a-upper cavity; 4b-lower cavity; 5-self-stabilizing device; 51-first rotating component; 52-second rotating component; 53-third rotating component; 54-base; 6-wind meter; 61-main body; 62-base; 63-data line; 7-power supply; 8-signal interface;

[0032] 9 - Second support assembly; 91 - First support rod; 92 - Second support rod; 93 - Second mounting bracket; 94 - First connecting member; 95 - Second connecting member; 96 - Third connecting member;

[0033] 10 - First mounting bracket. Detailed implementation manner

[0034] In order to enable those skilled in the art of the present technology to better understand the solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific implementation manners.

[0035] Please refer to Figures 1-3 as shown in Figure 1 a schematic diagram of the wind measurement device 200 carried on the unmanned aerial vehicle 100 in the embodiment of the present application; Figure 2 is Figure 1 a schematic diagram of the wind measurement device 200 installed on the top of the unmanned aerial vehicle 100 in Figure 3 is Figure 2 a schematic diagram of the wind measurement device 200 in

[0036] The wind measurement device 200 in this embodiment is used to be carried on the unmanned aerial vehicle 100, specifically on the top of the unmanned aerial vehicle 100. Among them, the wind measurement device 200 includes an equipment cabin 1 for being arranged on the top of the unmanned aerial vehicle 100, and the equipment cabin 1 is of a shell structure. A first mounting bracket 10 is arranged at the bottom of the equipment cabin 1 for directly connecting to the top of the airframe 102 of the unmanned aerial vehicle 100. The first mounting bracket 10 is of a hollow columnar structure, and the first mounting bracket 10 and the unmanned aerial vehicle 100 can be fixed by screws passing through the hollow column. The wind measurement device 200 further includes an anemometer 6, a self-stabilizing device 5, and a controller 3. The controller 3 is arranged in the equipment cabin 1, and the equipment cabin 1 can provide protection for the controller 3. The self-stabilizing device 5 is installed in the equipment cabin 1, and the anemometer 6 is installed on the self-stabilizing device 5.

[0037] Please continue to refer to Figures 4-6 for understanding Figure 4 a three-dimensional structure schematic diagram of the wind measurement device 200 carried on the unmanned aerial vehicle 100 in the embodiment of the present application; Figure 5 is Figure 4 an enlarged view of the position of the wind measurement device 200 in Figure 6 is Figure 5 a schematic diagram of the self-stabilizing device 5 in

[0038] The self-stabilizing device 5 in this embodiment includes a first rotating member 51, a second rotating member 52, and a third rotating member 53. Among them, the rotation axes of the first rotating member 51 and the second rotating member 52 extend horizontally and are perpendicular to each other, that is, the first rotating member 51 and the second rotating member 52 rotate in the vertical plane, and the rotation axis of the third rotating member 53 extends vertically, that is, the third rotating member 53 rotates in the horizontal plane. The third rotating member 53 is installed in the equipment cabin 1, the second rotating member 52 is connected to the third rotating member 53, the first rotating member 51 is connected to the second rotating member 52, and the anemometer 6 is installed on the first rotating member 51. Defining the XY plane as the horizontal plane and Z as the vertical direction, the self-stabilizing device 5 can realize rotation in the XY plane, YZ plane, and XZ plane, so as to drive the anemometer 6 to realize adjustment at any angle. The first rotating member 51, the second rotating member 52, and the third rotating member 53 can be rotating motors for realizing rotation, and the rotation accuracy can reach 0.1°.

[0039] After the drone 100 takes off, when the attitude of the drone 100 changes due to external environmental changes, the self-stabilizing device 5 will make compensation to ensure that the anemometer 6 is in a relatively stable state. The self-stabilizing device 5 also includes a gyroscope and an acceleration sensor not shown in the figure, which respectively sense the rotation state of the anemometer 6 and measure the angular velocity and linear acceleration. The gyroscope and the acceleration sensor transmit signals to the controller 3. The controller 3 monitors the data of the gyroscope and the acceleration sensor in real time, and performs calculations and adjustments to control the rotation of the first rotating member 51, the second rotating member 52, and the third rotating member 53 to maintain the stable state of the anemometer 6.

[0040] In this embodiment, the anemometer 6 is installed on the first rotating member 51, and a shock-absorbing sponge glue can be provided between the anemometer 6 and the first rotating member 51 to reduce the influence of the vibration generated by the self-stabilizing device 5 on the detection of the anemometer 6.

[0041] The anemometry device 200 in this embodiment can adjust the attitude of the anemometer 6 through the self-stabilizing device 5, so that the anemometer 6 is less affected by the wind and the tilt angle of the drone 100, and maintains a relatively stable attitude for wind speed measurement, so as to flexibly measure the wind following the drone. Moreover, the anemometer 6 can be installed on the top of the drone 100 through the equipment cabin 1, so that it will not be affected by the airflow generated by the wings 101 of the drone 100 during flight, improving the accuracy of the detection data of the anemometer 6.

[0042] It should be noted that, as Figure 5As shown in the figure, the third rotating component 53 in this embodiment is arranged in the equipment cabin 1. An opening 1a can be formed at the top of the equipment cabin 1, and the third rotating component 53 of the self-stabilizing device 5 can be placed into the equipment cabin 1 from the position of the opening 1a. At this time, the equipment cabin 1 can include a top cover plate 12. After the third rotating component 53 is installed into the equipment cabin 1 from the opening 1a, the opening 1a can be covered by the top cover plate 12 to reduce the entry of wind, dust, etc. The top cover plate 12 can be fixed to the equipment cabin 1 through fastening screws. It can be known that in order to ensure smooth installation, the opening 1a is set relatively large. However, the third rotating component 53 also needs to be connected to the second rotating component 52, and the second rotating component 52 will rotate relative to the third rotating component 53. To avoid interference, the top cover plate 12 can be set to have an area smaller than that of the opening 1a, and the position corresponding to the third rotating component 53 in the opening 1a can be left uncovered to leave a certain amount of moving space.

[0043] Such a setting is because the inventor found during the research process that if the self-stabilizing device 5 carrying the anemometer 6 is externally arranged above the equipment cabin 1, since the third rotating component 53 located at the bottom needs to bear the loads of the first rotating component 51, the second rotating component 52, and the anemometer 6, when the unmanned aerial vehicle 100 takes off and flies in the presence of relatively strong wind speeds, the third rotating component 53 may undergo flutter. After the third rotating component 53 is placed into the equipment cabin 1, due to the shielding and protection of the equipment cabin 1 for the third rotating component 53, the third rotating component 53 is not affected by the wind and flutter can be avoided, thereby ensuring the stability of the self-stabilizing device 5 and correspondingly facilitating the accuracy of the detection by the anemometer 6.

[0044] Specifically, as Figure 2 、 3 shown, a first support assembly 4 is arranged inside the equipment cabin 1 in this embodiment. The first support assembly 4 includes a first side plate 41 and a second side plate 42 arranged opposite to each other. The first side plate 41 and the second side plate 42 can be supported between the top and the bottom of the equipment cabin 1. The self-stabilizing device 5 further includes a base 54, and the third rotating component 53 is installed on the base 54. The base 54 is clamped between the first side plate 41 and the second side plate 42. In this way, the first side plate 41 and the second side plate 42 of the first support assembly 4 can clamp the base 54 in a relatively stable state, thereby achieving reliable positioning and protection for the third rotating component 53 and ensuring the self-stabilizing device 5 to maintain the attitude of the anemometer 6. In addition, the base 54 and the first support assembly 4 can be connected and fixed through locking screws to ensure the stability of the position of the self-stabilizing device 5.

[0045] Furthermore, the first support assembly 4 in this embodiment further includes a support plate 43, and the support plate 43 connects the first side plate 41 and the second side plate 42. As Figure 3As shown, the first support assembly 4 is an H-shaped assembly. At this time, the support plate 43 divides the space between the first side plate 41 and the second side plate 42 into an upper cavity 4a and a lower cavity 4b. The base 54 of the self-stabilizing device 5 is located in the upper cavity 4a. The wind measurement device 200 further includes a power source 7 capable of supplying power to the self-stabilizing device 5, and the power source 7 is arranged in the lower cavity 4b. At this time, the support plate 43 can be provided with wire holes to establish a power supply connection between the power source 7 and the self-stabilizing device 5. Of course, it is also possible that the power supply wire of the power source 7 bypasses the support plate 43 and is connected to the self-stabilizing device 5. The first support assembly 4 is arranged in this way to make full use of the space between the first side plate 41 and the second side plate 42, and at the same time facilitate the power supply to the self-stabilizing device 5.

[0046] Continue to refer to Figure 3 , in this embodiment, the controller 3 for controlling the self-stabilizing device 5 is arranged on the side of the first side plate 41 away from the second side plate 42. The side of the first side plate 41 and the second side plate 42 away from the space between them is defined as the outer side, and the side facing the space between them is defined as the inner side. Then, the controller 3 is arranged on the outer side of the first side plate 41. Connection holes 411 (shown in Figure 4 ) can be provided on the first side plate 41 for installing and fixing the controller 3. At this time, the power source 7 located inside the first side plate 41 can also supply power to the controller 3, so that one power source 7 supplies power to multiple electrical components, simplifying the structure. Of course, a separate power source 7 can also be provided to supply power to the controller 3, and the controller 3 is connected to the self-stabilizing device 5 through a control line to perform rotation control on each rotating component according to the data detected by the gyroscope and the acceleration sensor.

[0047] The wind measurement device 200 in this embodiment further includes a data acquisition instrument 2. The data acquisition instrument 2 is arranged on the side of the second side plate 42 away from the first side plate 41, that is, arranged on the outer side of the second side plate 42. In this way, the first support assembly 4 is used more effectively, and the space in the equipment cabin 1 is reasonably utilized. The controller 3 and the data acquisition instrument 2 are arranged on both sides of the first support assembly 4, making the structure in the equipment cabin 1 relatively compact and reducing the volume of the equipment cabin 1. The data acquisition instrument 2 is signal-connected to the anemometer 6. Specifically, a data line 63 is arranged to connect to the data acquisition instrument 2, that is, signals such as the wind speed collected by the anemometer 6 are transmitted to the data acquisition instrument 2 and stored by the data acquisition instrument 2. It can be seen that the signal of the anemometer 6 can also be directly transmitted to the controller 3, and the controller 3 integrates a data acquisition module. Setting the data acquisition instrument 2 separately facilitates the export of the signal of the data acquisition instrument 2 from the equipment cabin 1. The above-mentioned power source 7 can conveniently supply power to the data acquisition instrument 2 at the same time.

[0048] As Figure 3As shown, the anemometer 6 includes a main body part 61, a base 62, and a data line 63. The base 62 is located below the main body part 61. The sensing element for wind measurement is arranged in the main body part 61, and the detected data is transmitted outward through the data line 63. Specifically, the data line 63 passes through the base 62 to be inserted into the equipment cabin 1 and connected to the data acquisition instrument 2. On the one hand, the base 62 can protect the data line 63, and on the other hand, it can act as a counterweight to facilitate the structural stability of the anemometer 6.

[0049] As Figure 5 shown, a signal interface 8 facing outward is provided on the side wall of the equipment cabin 1, and the signal interface 8 is signal-connected to the data acquisition instrument 2. With such a setting, the signal interface 8 can be docked according to needs through a signal line connector to export wind measurement data such as wind speed signals in the data acquisition instrument 2 to a data storage disk or a host computer for calculation analysis, research, reference, etc. It can be seen that these signals detected by the anemometer 6 can also be wirelessly transmitted, but the signal transmission is more stable and reliable through the connection of the data line 63.

[0050] In addition, as Figure 5 shown, a battery compartment cover 11 is also provided on the side wall of the equipment cabin 1. After the battery compartment cover 11 is opened, the battery 7 arranged in the lower cavity 4b of the first support assembly 4 can be replaced, which is convenient for operation.

[0051] Please continue to refer to Figure 7 、 8 Figure 8 For Figure 7 a schematic diagram of another perspective of the wind measurement device in Figure 7 This is a schematic diagram of the structure of the wind measurement device 200 in the second embodiment of the present application, mainly showing the anemometer 6, the self-stabilizing device 5, and the second support assembly 9; Figure 8 For Figure 7 a schematic diagram of another perspective of the wind measurement device in

[0052] The wind measurement device 200 in this embodiment also includes a controller 3 and an anemometer 6. The controller 3 and the anemometer 6 can be arranged below the second support assembly 9, Figure 7It is not shown in the figure. The second support assembly 9 includes a first support rod 91 arranged vertically. The self-stabilizing device 5 is installed at one end of the first support rod 91, specifically at the upper end of the first support rod 91. A first connecting member 94 can be sleeved on the upper end of the first support rod 91. The first connecting member 94 can be a block structure and can be fixed to the first support rod 91 by press-fitting or welding. The self-stabilizing device 5 also includes a first rotating member 51 and a second rotating member 52 which are the same as those in the first embodiment. The second rotating member 52 is fixed to the first support rod 91, specifically fixed to the first connecting member 41 by fastening screws. The second support assembly 9 further includes a second support rod 92 arranged horizontally. The lower end of the first support rod 92 is connected to one end of the second support rod 92. The first support rod 91 and the second support rod 92 form an L-shaped frame structure. The first support rod 91 and the second support rod 92 are connected by a second connecting member 95. The second connecting member 95 includes a vertical mounting hole and a horizontal mounting hole. The lower end of the first support rod 91 is inserted into the vertical mounting hole, and one end of the second support rod 92 is inserted into the horizontal mounting hole.

[0053] The second support rod 92 is for installing to the drone 100. Specifically, the second support assembly 9 further includes a second mounting bracket 93. The second support rod 92 is fixed to the second mounting bracket 93, and the second mounting bracket 93 can be installed and fixed to the top of the drone 100. The second mounting bracket 93 is as Figure 7 shown, including a mounting plate and a plurality of connecting columns located below the mounting plate. The connecting columns are hollow columns for passing through screws and are fixed to the body 102 of the drone 100 to realize the stable support of the second support assembly 9 for the self-stabilizing device 5.

[0054] The second mounting bracket 93 in this embodiment and the first mounting bracket 10 in the first embodiment are both used for directly connecting to the top of the body 102 of the drone 100. At this time, the height of the front side of the first mounting bracket 10 can be higher than that of the rear side. Here, the front side and the rear side are consistent with the front and rear directions of the drone 100. With such a setting, the front side of the drone 100 can be set to be shorter and the rear side can be set to be higher to reduce wind resistance and maintain a better appearance. Correspondingly, the screws for fixing the first mounting bracket 10 and the second mounting bracket 93 to the drone 100 can also be set such that the front-side screws are longer and the rear-side screws are relatively shorter.

[0055] In this embodiment, the data collector 2 of the wind measurement device 200 is also connected to the controller 3 by signal. At this time, the first support rod 91 has an inner cavity, that is, the first support rod 91 is a tubular structure. The data line 63 of the anemometer 6 is inserted into the inner cavity of the first support rod 91. The data collector 2 is arranged below the first support rod 91. Then, after the data line 63 passes out from the lower end of the first support rod 91, it can be directly connected to the data collector 2 below for signal connection. The connection is simple and reliable, and the data line 63 is not easily displaced or entangled by the wind.

[0056] Compared with the first embodiment, the third rotating member 53 is not provided in the self-stabilizing device 5 in the second embodiment. At this time, the rotation of the anemometer 6 in the horizontal plane is controlled by the carried unmanned aerial vehicle 100. That is, the unmanned aerial vehicle 100 is equipped with a GPS system (Global Positioning System). During the flight, the unmanned aerial vehicle 100 can also rotate in the horizontal plane to determine the direction. However, in the first embodiment, due to the setting of the third rotating member 53, the position of the self-stabilizing device 5 in the horizontal plane can be controlled independently by the controller 3 without relying on the unmanned aerial vehicle 100. There may be a certain deviation in the direction of the unmanned aerial vehicle 100 in the horizontal plane during the flight. In the first embodiment, the angle control in the horizontal direction is carried out independently, which can make the control of the self-stabilizing device 5 more stable, and the attitude of the anemometer 2 is accordingly more stable.

[0057] In addition, in the second embodiment, the controller for controlling the rotation of the first rotating member 51 and the second rotating member 52 can be arranged on the self-stabilizing device 5. As Figure 7 shown, the first rotating member 51 can be connected to the second rotating member 52 through a support 55, and the controller and the power supply can be fixed to the support 55. Compared with the second embodiment, in the first embodiment, the controller 3, the power supply 7, etc. are installed in the equipment cabin 1, which can reduce the load of the self-stabilizing device 5 and is more conducive to the stable control of the attitude.

[0058] For the above-mentioned embodiments, since the wind measurement device 200 is carried on the top of the fuselage 102 of the unmanned aerial vehicle 100, the self-stabilizing device 5 needs to bear the load. Therefore, when the first rotating member 51, the second rotating member 52, and the third rotating member 53 of the self-stabilizing device 5 adopt rotating motors, the housings of the rotating motors are all made of alloy materials to meet the load-bearing requirements and prevent deformation from affecting the attitude stability.

[0059] The embodiment of the present application also provides an unmanned aerial vehicle 100. The unmanned aerial vehicle 100 includes a fuselage 102 and wings 101 extending from the fuselage. The wind measurement device 200 described in any of the above embodiments is specifically installed on the top of the fuselage 102, and has the same technical effects as above, and will not be repeated here.

[0060] The drone 100 equipped with the wind measurement device 200 in this embodiment can increase the reliability of using the drone 100 to measure data such as wind speed and wind direction, thus eliminating the need for expensive fixed iron towers and methods such as deploying lidar for wind measurement.

[0061] By using the drone 100, accurate real-time measurements of data such as wind speed and wind direction at any time, at any required geographical location (such as mountains, oceans, uninhabited deserts, etc.), and at any altitude can be quickly obtained.

[0062] The drone 100 equipped with the wind measurement device 200 in the embodiment of this application can be applied to the field of wind power generation to provide accurate meteorological data such as wind force and wind direction for the wind power generation field, which is supportively helpful for the site selection of wind farms, the design and commissioning of wind turbines, and the software calibration after the operation of wind farms, so as to reduce the measurement cost and improve the convenience of measurement.

[0063] In this article, specific examples are used to elaborate on the principle and implementation manner of this application. The description of the above embodiments is only used to help understand the method and its core idea of this application. It should be noted that for those of ordinary skill in the art of this technology, without departing from the principle of this application, several improvements and modifications can be made to this application, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. An anemometry device for being carried on an unmanned aerial vehicle, characterized in that, the anemometry device includes an anemometer, a self-stabilizing device and a controller. The self-stabilizing device is used for being installed on the top of the unmanned aerial vehicle. The self-stabilizing device includes a first rotating member and a second rotating member. The rotation axes of the first rotating member and the second rotating member extend horizontally and are perpendicular to each other. The first rotating member is connected to the second rotating member. The anemometer is installed on the first rotating member. The controller is used for controlling the rotation of the first rotating member and the second rotating member.

2. The anemometry device according to claim 1, characterized in that, the anemometry device includes an equipment cabin. The self-stabilizing device further includes a third rotating member. The controller further controls the rotation of the third rotating member. The second rotating member is connected to the third rotating member. The rotation axis of the third rotating member extends vertically. The third rotating member is arranged inside the equipment cabin.

3. The anemometry device according to claim 2, characterized in that, a first support assembly is arranged inside the equipment cabin. The first support assembly includes a first side plate and a second side plate. The self-stabilizing device includes a base. The third rotating member is installed on the base. The base is clamped between the first side plate and the second side plate.

4. The anemometry device according to claim 3, characterized in that, the first support assembly further includes a support plate. The support plate connects the first side plate and the second side plate. The support plate divides the space between the first side plate and the second side plate into an upper cavity and a lower cavity. The base is located in the upper cavity. The anemometry device further includes a power supply for supplying power to the self-stabilizing device. The power supply is arranged in the lower cavity.

5. The anemometry device according to claim 3 or 4, characterized in that, the controller is arranged on a side of the first side plate away from the second side plate.

6. The anemometry device according to claim 5, characterized in that, it further includes a data acquisition instrument. The data acquisition instrument is arranged on a side of the second side plate away from the first side plate. The data acquisition instrument is in signal connection with the anemometer.

7. The anemometry device according to claim 6, characterized in that, a signal interface facing outward is arranged on the side wall of the equipment cabin. The signal interface is in signal connection with the data acquisition instrument.

8. The anemometry device according to any one of claims 2-4, 6-7, characterized in that, the first rotating member, the second rotating member and the third rotating member are all rotating motors. The housing of the rotating motor is made of alloy material.

9. The anemometry device according to claim 1, characterized in that, the anemometry device includes a second support assembly. The second support assembly includes a first support rod arranged vertically and a second support rod arranged horizontally. The self-stabilizing device is installed at one end of the first support rod. The other end of the first support rod is connected to the second support rod. The second support rod is used for being installed on the top of the unmanned aerial vehicle.

10. The anemometry device according to claim 9, characterized in that, The equipment cabin is provided with a data collector, which is located below the first support rod. The first support rod has an inner cavity, and the data line of the anemometer passes through the inner cavity of the first support rod and is signal-connected to the data collector.

11. The anemometry device according to any one of claims 1-4, 6-7, 9, 10, characterized in that, a shock-absorbing sponge glue is provided between the anemometer and the first rotating member.

12. The anemometry device according to any one of claims 1-4, 6-7, 9, 10, characterized in that, the anemometry device includes a mounting bracket for fixing the equipment cabin to the unmanned aerial vehicle, and the height of the front side of the mounting bracket is higher than the height of the rear side thereof.

13. An unmanned aerial vehicle, characterized in that, the unmanned aerial vehicle includes a fuselage and wings, and the anemometry device according to any one of claims 1-12 is carried on the top of the fuselage.

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