A non-orthogonal transducer array three-dimensional ultrasonic wind speed and direction instrument capable of being mounted on a drone

Abstract

The application discloses a non-orthogonal transducer array three-dimensional ultrasonic wind speed and direction instrument which can be carried on a unmanned aerial vehicle and applied to the field of wind speed and direction instruments, and the non-orthogonal transducer array is adopted to reduce the influence of turbulence on wind measurement accuracy; when the turbulence degree generated by one group of transducers is relatively large, the other two groups of transducers can compensate the data, so that high-precision wind speed and direction measurement is realized; meanwhile, when the unmanned aerial vehicle encounters strong wind, the probe fixing rod will be broken, so that the unmanned aerial vehicle is prevented from losing control due to the large wind area of the orthogonal annular support, and the fixed base plate and the elastic thin rod are arranged to recycle the broken and fallen orthogonal annular support and ultrasonic probe, so that the high-altitude falling object is not easy to form, and the orthogonal annular support and the ultrasonic probe are effectively protected, the subsequent recycling and reuse of the orthogonal annular support and the ultrasonic probe are facilitated, and the wind direction and speed detection in strong convection weather such as strong wind is applicable.

Description

Technical Field

[0001] This invention relates to the field of anemometers, and in particular to a three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a drone. Background Technology

[0002] The basic measurement principle of an acoustic anemometer is based on the time difference of ultrasonic waves propagating in the air with and against the wind to calculate wind speed and direction. By increasing the number of ultrasonic transducers and rationally arranging their positions, three-dimensional wind field measurement can be achieved. By measuring the wind speed components in the X, Y, and Z directions, simultaneous measurement of horizontal and vertical wind direction can be realized. Some models can also measure the speed of sound based on the propagation time of the ultrasonic signal and derive the virtual temperature after crosswind effect correction.

[0003] The utility model with publication number CN204694730U discloses a three-dimensional ultrasonic wind direction and speed meter. Three pairs of ultrasonic probes are arranged in a three-dimensional spatial distribution with upward and downward beams. It can measure wind direction and speed in both horizontal and vertical directions, and can measure wind direction and speed along the X, Y, and Z axes with and against the wind. The measured wind direction and speed data have small errors.

[0004] Most existing three-dimensional anemometers adopt a vertically orthogonal arrangement, consisting of three sets of ultrasonic transducer arrays based on a spatial rectangular coordinate system. The design of this array ignores the influence of turbulence interference, and the turbulence inside the array is relatively high. Based on the actual wind field environment, the wind field is determined to be a viscous compressible unsteady Newtonian flow field. This flow field is quite sensitive to the size of the transducers in the field and the angle between the transducer groups. The greater the transducer blocking effect and the denser the transducer groups, the greater the shadow effect generated by the wind passing through the inside of the array, the higher the turbulence, and the greater the detection error. Summary of the Invention

[0005] The core of this invention lies in reducing the impact of turbulence on wind measurement accuracy through a non-positive transducer array. When the turbulence generated by one set of transducers is large, the other two sets of transducers can compensate for the data, thereby achieving high-precision wind speed and direction measurement.

[0006] To solve the above problems, the present invention adopts the following technical solution.

[0007] A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a drone includes a fixed base, an electrical cylinder fixedly connected to the upper end of the fixed base, a probe fixing rod fixedly connected to the upper end of the electrical cylinder, an orthogonal ring bracket fixedly connected to the upper end of the probe fixing rod, and four ultrasonic probes fixedly connected to the orthogonal ring bracket. The four ultrasonic probes are distributed at the four vertices of a regular tetrahedron, and the center lines of the ultrasonic waves generated by the multiple ultrasonic probes converge at the center of the regular tetrahedron.

[0008] When the drone is hovering, taking two ultrasonic sensors in the east-west direction as an example, the propagation time of the ultrasonic waves is as follows when there is a tailwind:

[0009] ;

[0010] When there is a headwind, the propagation time of ultrasound is:

[0011] ;

[0012] Where C is the speed of sound, L is the distance the ultrasonic wave travels, and V x Let V be the component of the wind speed in the east-west direction. The above two equations can be used to calculate V. x :

[0013] ;

[0014] t1 and t2 are the transmission times of the ultrasonic waves when traveling with the wind and against the wind in the east-west direction, respectively;

[0015] Similarly, the north-south wind speed component Vy can be obtained:

[0016] ;

[0017] t3 and t4 represent the transmission times of the ultrasonic waves in the north-south direction with and against the wind, respectively. Since the sensors are pairwise orthogonal, the theoretical two-dimensional wind speed V and wind direction angle θ can be calculated as follows:

[0018] ;

[0019] ;

[0020] Four ultrasonic probes are located at the four vertices of a regular tetrahedron. The center lines of the ultrasonic waves emitted by the four probes intersect at the center of the tetrahedron. The three spatial dimensions are normalized to the path of the transducer group according to the angle analysis formula. The wind speed component on each path is measured by the transducer using the time difference method. Finally, the three-dimensional wind speed and wind direction values ​​are determined using the obtained normalization formula.

[0021] Furthermore, the circuit box contains the complete circuit, which includes a core processing and control circuit, a power supply circuit, an ultrasonic drive receiving circuit, a signal acquisition circuit, a storage circuit, and a display circuit. Each circuit is connected to the core chip through corresponding I / O pins. The core processing and control circuit sends ultrasonic drive signals and organizes the installation sequence of the four probes according to a certain logic to transmit and receive ultrasonic signals. The multiplexer selects a set of ultrasonic transceiver signals according to a certain logic and sends them to the amplifier. Then, the phase difference is calculated by the comparator in the core processing and control circuit, and the time difference is calculated.

[0022] Furthermore, a fixed base is fixedly connected to the lower end of the fixed base, and multiple elastic thin rods are fixedly connected to the inner wall of the fixed base. The multiple elastic thin rods intersect each other to form a three-dimensional spatial structure. A hollow cavity is carved inside the probe fixing rod, and a windproof groove is carved on the inner wall of the hollow cavity. Threaded fixing blocks are threaded to the upper and lower ends of the hollow cavity, and an elastic cable is fixedly connected between the two threaded fixing blocks. The elastic cable is in a relaxed state.

[0023] Furthermore, the probe fixing rod includes a fixed rod body and a movable rod body that match each other, and the windproof groove is located in the movable rod body. The fixed rod body is fixedly connected to the circuit cylinder, and the movable rod body is fixedly connected to the orthogonal ring bracket. The fixed rod body and the movable rod body are threadedly connected, so that the threaded fixing block and the elastic cable can be installed normally, which facilitates the subsequent replacement of the damaged probe fixing rod.

[0024] Furthermore, the elastic cable has multiple loops, each of which is fixedly connected to an elastic buckle. When the orthogonal ring support breaks, it will pull the elastic cable. When the elastic cable straightens, it will pull the orthogonal ring support, reducing the falling speed of the orthogonal ring support. This makes it less likely for the orthogonal ring support to have an excessive impact on the fixed chassis, reducing the impact on the drone's flight and increasing the safety of the drone's flight.

[0025] Furthermore, the different limit stresses of the multiple elastic buckles allow for multi-stage deceleration of the orthogonal ring support, increasing its protective effect and preventing it from falling too fast.

[0026] Furthermore, the elastic thin rod includes a rod body with multiple pre-fabricated grooves to buffer the orthogonal ring support and further enhance the protection of the orthogonal ring support.

[0027] Furthermore, the depth of the multiple prefabricated grooves increases with the distance between them and the fixed connection ends to the inner wall of the fixed chassis, making it easier for the elastic rod to retain more residual effective parts, and allowing the elastic rod to be recycled and reused multiple times.

[0028] Compared with the prior art, the advantages of this invention are:

[0029] This scheme uses a non-positive transducer array to reduce the impact of turbulence on wind measurement accuracy. When the turbulence generated by one set of transducers is large, the other two sets of transducers can compensate for the data, thereby achieving high-precision wind speed and direction measurement.

[0030] Meanwhile, when the drone encounters strong winds, the probe fixing rod will break, preventing the drone from going out of control due to the large wind-exposed area of ​​the orthogonal ring bracket. A fixed chassis and elastic thin rod are installed to recover the broken orthogonal ring bracket and ultrasonic probe, reducing the risk of falling objects from high altitudes and accidents. This also effectively protects the orthogonal ring bracket and ultrasonic probe, making the orthogonal ring bracket less prone to deformation, the ultrasonic probe angle less prone to change, and the ultrasonic probe less prone to failure. This facilitates the subsequent recovery and reuse of the orthogonal ring bracket and ultrasonic probe, making it suitable for wind direction and wind speed detection in strong convective weather such as strong winds. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the structure of a three-dimensional ultrasonic anemometer with a non-positive exchanger array according to the first embodiment.

[0032] Figure 2 The basic measurement principle of wind speed and direction using the time difference method in existing technologies. Figure 1 ;

[0033] Figure 3 The basic measurement principle of wind speed and direction using the time difference method in existing technologies. Figure 2 ;

[0034] Figure 4 This is a circuit block diagram of the core circuit of the non-positive exchanger array three-dimensional ultrasonic anemometer of the present invention.

[0035] Figure 5 This is a schematic diagram of the structure of a three-dimensional ultrasonic anemometer with a non-positive exchanger array according to the second embodiment.

[0036] Figure 6 This is a cross-sectional schematic diagram of a three-dimensional ultrasonic anemometer with a non-positive exchanger array according to the first embodiment.

[0037] Figure 7 for Figure 6 Schematic diagram of the structure at point A;

[0038] Figure 8 for Figure 7 Schematic diagram of the structure at point B;

[0039] Figure 9 This is a schematic diagram of the structure of the elastic rod of the present invention;

[0040] Figure 10 This is a schematic diagram comparing the dimensions of the prefabricated groove in the elastic rod of the present invention.

[0041] Explanation of the labels in the diagram:

[0042] 1. Fixed base, 2. Circuit cylinder, 3. Probe fixing rod, 301. Fixed rod body, 302. Movable rod body, 303. Threaded fixing block, 304. Elastic cable, 305. Elastic buckle, 306. Windproof groove, 4. Orthogonal ring bracket, 5. Ultrasonic probe, 6. Fixed chassis, 7. Elastic thin rod, 701. Rod body, 702. Precast groove. Detailed Implementation

[0043] The technical solutions will now be clearly and completely described with reference to the accompanying drawings in the embodiments of the present invention.

[0044] First implementation method:

[0045] Please see Figure 1 A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a drone includes a fixed base 1, which is fixedly connected to the upper platform of the drone by screws or clips to reduce the influence of airflow generated by the drone's fan blades on the anemometer's detection. An electrical cylinder 2 is fixedly connected to the upper end of the fixed base 1, and a probe fixing rod 3 is fixedly connected to the upper end of the electrical cylinder 2. An orthogonal ring bracket 4 is fixedly connected to the upper end of the probe fixing rod 3. Four ultrasonic probes 5 are fixedly connected to the orthogonal ring bracket 4. The four ultrasonic probes 5 are distributed at the four vertices of a regular tetrahedron, and the center lines of the ultrasonic waves generated by the multiple ultrasonic probes 5 converge at the center of the regular tetrahedron.

[0046] Please see Figure 2 - Figure 3 When ultrasound propagates in the air, there is a time difference between propagation with the wind and against the wind. The time difference method is used to measure the transmission time of ultrasound in these two states, and the wind speed and direction are calculated by the formula. This is the most commonly used method in ultrasonic wind measurement systems. Taking two-dimensional wind field measurement as an example, a pair of ultrasonic sensors that transmit and receive each other are placed along the east-west and north-south directions, and the two pairs of ultrasonic sensors are kept at equal distances and perpendicular to each other.

[0047] When the drone is hovering, taking two ultrasonic sensors in the east-west direction as an example, the propagation time of the ultrasonic waves is as follows when there is a tailwind:

[0048] ;

[0049] When there is a headwind, the propagation time of ultrasound is:

[0050] ;

[0051] Where C is the speed of sound, L is the distance the ultrasonic wave travels, and V x Let V be the component of the wind speed in the east-west direction. The above two equations can be used to calculate V. x :

[0052] ;

[0053] t1 and t2 are the transmission times of the ultrasonic waves when traveling with the wind and against the wind in the east-west direction, respectively;

[0054] Similarly, the north-south wind speed component Vy can be obtained:

[0055] ;

[0056] t3 and t4 represent the transmission times of the ultrasonic waves in the north-south direction with and against the wind, respectively. Since the sensors are pairwise orthogonal, the theoretical two-dimensional wind speed V and wind direction angle θ can be calculated as follows:

[0057] ;

[0058] .

[0059] Therefore, for this embodiment, the formula for calculating the wind speed component of each ultrasonic probe 5 is as follows:

[0060]

[0061] Where L i Let t be the propagation distance of the ultrasonic path of the i-th ultrasonic probe 5. i+ For tailwind propagation time, t i- For the time it takes to spread against the wind, v i This represents the wind speed component along the path.

[0062] Since the four ultrasonic probes 5 are located at the four vertices of the regular tetrahedron, the center lines of the ultrasonic waves they generate intersect at the center of the regular tetrahedron, thus satisfying the normalized projection relation:

[0063] Let the formal wind speeds in three-dimensional space be V. x V y and V z The unit direction vectors of the ultrasonic waves generated by the four ultrasonic probes 5 along the path are respectively , , and Then the path components and the three-dimensional wind speed satisfy:

[0064] ;

[0065] The above normalization constraints are satisfied:

[0066] + + + =0,

[0067] The total wind speed at this time is:

[0068] ;

[0069] At this time, the horizontal direction angle is:

[0070]

[0071] The elevation angle is:

[0072] .

[0073] In this embodiment, the non-positive exchanger array reduces the impact of turbulence on wind measurement accuracy. When the turbulence generated by one set of ultrasonic probes 5 is large, the other two sets of ultrasonic probes 5 can compensate for the data, thereby achieving high-precision wind speed and direction measurement.

[0074] Please see Figure 4 The complete circuit of the three-dimensional ultrasonic wind measurement system includes a core processing and control circuit, a power supply circuit, an ultrasonic drive and receiving circuit, a signal acquisition circuit, a storage circuit, and a display circuit. Each circuit is connected to the core chip through corresponding I / O pins. The core processing and control circuit sends ultrasonic drive signals and organizes the installation sequence of the four probes according to a certain logic to transmit and receive ultrasonic signals. The multiplexer selects a set of ultrasonic transceiver signals according to a certain logic and sends them to the amplifier. Then, the phase difference is calculated by the comparator in the core processing and control circuit, and the time difference is calculated.

[0075] When the drone is in motion, the distance the drone travels during the detection process can be measured by equipping the drone with a GPS positioning system. Then, the speed and direction of the drone's movement can be calculated. Substituting these values ​​into the above formula, the final wind speed can be corrected by calculating the tailwind and headwind speeds. This is a well-known technique to those skilled in the art, and they can perform the calculations based on existing technology.

[0076] Second implementation method:

[0077] Please see Figure 5 - Figure 8 The lower end of the fixed base 1 is fixedly connected to the fixed chassis 6. The fixed chassis 6 is fixedly connected to the upper platform of the drone by screws. Multiple elastic rods 7 are fixedly connected to the inner wall of the fixed chassis 6. The multiple elastic rods 7 are intersected to form a three-dimensional spatial structure. A hollow cavity is carved inside the probe fixing rod 3. A windproof groove 306 is carved on the inner wall of the hollow cavity. Threaded fixing blocks 303 are threaded to the upper and lower ends of the hollow cavity respectively. An elastic cable 304 is fixedly connected between two threaded fixing blocks 303. The elastic cable 304 is in a relaxed state.

[0078] When a drone encounters severe convective weather during wind speed and direction detection, the orthogonal ring support 4, with its large wind-receiving area, is easily blown off balance by strong winds at high altitudes, potentially causing the drone to crash. However, in this embodiment, when the drone encounters strong winds and the orthogonal ring support 4 experiences excessive wind force, the probe fixing rod 3 breaks along the direction of the windproof groove 306. The orthogonal ring support 4 and the ultrasonic probe 5 roll into the elastic thin rod 7. Due to the traction of the elastic cable 304, the broken portion of the probe fixing rod 3 and the orthogonal ring support 4 are less likely to fall too far and are more likely to fall into the fixed chassis 6, thus preventing them from crashing. The orthogonal ring bracket 4 and ultrasonic probe 5 are less likely to fall off the drone, thus reducing the risk of falling objects and accidents. After the orthogonal ring bracket 4 and ultrasonic probe 5 fall into the fixed chassis 6, they will compress the elastic rod 7 and deform it, allowing the orthogonal ring bracket 4 and ultrasonic probe 5 to fall to the bottom of the fixed chassis 6. The upper elastic rod 7, after being passed through by the orthogonal ring bracket 4, will quickly return to its original shape and reform the three-dimensional spatial structure, fixing the position of the orthogonal ring bracket 4 and ultrasonic probe 5. During the drone's flight, the orthogonal ring bracket 4 and ultrasonic probe 5 are less likely to shake and affect the normal operation of the drone.

[0079] Meanwhile, a through hole (not shown in the figure) should also be provided on the lower side wall of the fixed chassis 6 to facilitate the rapid drainage of rainwater in rainy weather, making it less likely for a large amount of water to accumulate inside the fixed chassis 6 and less likely to create a large load on the drone. This is a well-known technology to those skilled in the art, so it is not described in detail. Those skilled in the art can make reasonable designs according to the actual working environment to meet the usage requirements.

[0080] The probe fixing rod 3 includes a fixed rod body 301 and a movable rod body 302 that match each other, and the windproof groove 306 is located inside the movable rod body 302. The fixed rod body 301 is fixedly connected to the circuit tube 2, and the movable rod body 302 is fixedly connected to the orthogonal ring bracket 4. The fixed rod body 301 and the movable rod body 302 are threadedly connected, so that the threaded fixing block 303 and the elastic cable 304 can be installed normally, which facilitates the subsequent replacement of the damaged probe fixing rod 3.

[0081] The elastic cable 304 has multiple loops, each of which is fixedly connected to an elastic buckle 305. The elastic buckle 305 can be made of plastic. After the orthogonal ring support 4 breaks, it will pull the elastic cable 304. When the elastic cable 304 straightens, it will pull the orthogonal ring support 4, reducing the falling speed of the orthogonal ring support 4 and making it less likely for the orthogonal ring support 4 to fly out of the range of the elastic rod 7. If the speed of the orthogonal ring support 4 is still too fast, the elastic cable 304 can be pulled to break the elastic buckle 305, releasing the length of the elastic cable 304, so that the orthogonal ring support 4 can continue to move. By controlling the falling speed and distance of the orthogonal ring support 4 and the broken probe fixing rod 3 through the elastic cable 304 and multiple elastic buckles 305, the orthogonal ring support 4 and the fixed chassis 6 are less likely to have excessive impact, reducing the impact on the flight of the UAV and improving the safety of the UAV flight.

[0082] The multiple elastic buckles 305 have different ultimate stress levels, which can be achieved by controlling the thickness and material of the multiple elastic buckles 305. This allows the multiple elastic buckles 305 to break and fail in stages. At the same time, it can also take effect under different flight and fall speeds of the orthogonal ring bracket 4, and perform multi-stage deceleration on the orthogonal ring bracket 4, thereby increasing the protection effect on the orthogonal ring bracket 4 and making it less likely for the orthogonal ring bracket 4 to fall too fast.

[0083] Please see Figure 9 - Figure 10 The elastic rod 7 includes a rod body 701 with multiple pre-made grooves 702. When the orthogonal ring support 4 falls into the fixed base 6, if the orthogonal ring support 4 falls too fast and collides strongly with the elastic rod 7, the elastic rod 7 can break along the pre-made grooves 702 to buffer the orthogonal ring support 4 and further increase the protection of the orthogonal ring support 4. The depth of the multiple pre-made grooves 702 increases with the distance between them and the fixed connection ends to the inner wall of the fixed base 6, making it easier for the elastic rod 7 to break away from the inner wall of the fixed base 6 under the impact of the orthogonal ring support 4. This makes it easier for the elastic rod 7 to retain more of its fragments and allows it to be recycled and reused multiple times.

[0084] In this embodiment, the structure of the probe fixing rod 3 has been further improved. When the drone encounters strong winds, the probe fixing rod 3 will break, avoiding the phenomenon of the drone going out of control due to the large wind-receiving area of ​​the orthogonal ring bracket 4. A fixed chassis 6 and elastic thin rod 7 are set to recover the broken orthogonal ring bracket 4 and ultrasonic probe 5, which is less likely to form falling objects from high altitudes and cause safety accidents. At the same time, it also effectively protects the orthogonal ring bracket 4 and ultrasonic probe 5, making the orthogonal ring bracket 4 less prone to deformation, the ultrasonic probe 5 less prone to change in angle, and the ultrasonic probe 5 less prone to failure. This facilitates the subsequent recovery and reuse of the orthogonal ring bracket 4 and ultrasonic probe 5, and is suitable for wind direction and wind speed detection in strong convective weather such as strong winds.

[0085] In particular, in this embodiment, by controlling the depth of the windproof groove 306 and the material of the movable rod 302, the maximum wind force that the probe fixing rod 3 can withstand when it breaks can be controlled. Thus, the windproof groove 306 can be set according to the power of the UAV, thereby enabling the probe fixing rod 3 to break in advance before the UAV loses control. The specific design method of the depth of the windproof groove 306 is a well-known technology to those skilled in the art, and therefore is not disclosed in detail in this application.

[0086] The above description is merely a preferred embodiment of the present invention; it encompasses all the protection scope of the present invention. Any equivalent substitutions or modifications made by those skilled in the art within the technical scope disclosed in the present invention, based on the technical solutions and improved concepts of the present invention, should be covered within the protection scope of the present invention.

Claims

1. A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV, comprising a fixed base (1), characterized in that: The upper end of the fixed base (1) is fixedly connected to the circuit cylinder (2), the upper end of the circuit cylinder (2) is fixedly connected to the probe fixing rod (3), the upper end of the probe fixing rod (3) is fixedly connected to the orthogonal ring bracket (4), and four ultrasonic probes (5) are fixedly connected on the orthogonal ring bracket (4). The four ultrasonic probes (5) are distributed at the four vertices of the regular tetrahedron, and the ultrasonic center lines generated by the multiple ultrasonic probes (5) intersect at the center of the regular tetrahedron. When the drone is hovering, taking two ultrasonic sensors in the east-west direction as an example, the propagation time of the ultrasonic waves is as follows when there is a tailwind: ； When there is a headwind, the propagation time of ultrasound is: ； Where C is the speed of sound, L is the distance the ultrasonic wave travels, and V x Let V be the component of wind speed in the east-west direction. The above two equations can be used to calculate V. x : ； t1 and t2 are the transmission times of the ultrasonic waves when traveling with the wind and against the wind in the east-west direction, respectively; Similarly, the north-south wind speed component Vy can be obtained: ； t3 and t4 represent the transmission times of the ultrasonic waves in the north-south direction with and against the wind, respectively. Since the sensors are pairwise orthogonal, the theoretical two-dimensional wind speed V and wind direction angle θ can be calculated as follows: ； ； The four ultrasonic probes (5) are located at the four vertices of the regular tetrahedron. The center lines of the ultrasonic waves emitted by the four ultrasonic probes (5) intersect at the center of the regular tetrahedron. The three dimensions of space are normalized to the path of the transducer group according to the angle analysis formula. The wind speed component on each path is measured by the transducer using the time difference method. Finally, the three-dimensional wind speed and wind direction values ​​are determined by the obtained normalization formula.

2. The three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV according to claim 1, characterized in that: The circuit tube (2) contains a complete circuit, which includes a core processing and control circuit, a power supply circuit, an ultrasonic drive receiving circuit, a signal acquisition circuit, a storage circuit, and a display circuit. Each circuit is connected to the core chip through a corresponding I / O pin.

3. The three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV according to claim 1, characterized in that: The lower end of the fixed base (1) is fixedly connected to a fixed chassis (6). Multiple elastic rods (7) are fixedly connected to the inner wall of the fixed chassis (6). The multiple elastic rods (7) intersect each other to form a three-dimensional spatial structure. A hollow cavity is carved inside the probe fixing rod (3). A windproof groove (306) is carved on the inner wall of the hollow cavity. Threaded fixing blocks (303) are threaded to the upper and lower ends of the hollow cavity respectively. An elastic cable (304) is fixedly connected between two threaded fixing blocks (303). The elastic cable (304) is in a relaxed state.

4. A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV, as described in claim 3, is characterized in that: The probe fixing rod (3) includes a fixed rod body (301) and a movable rod body (302) that match each other, and the windproof groove (306) is located inside the movable rod body (302). The fixed rod body (301) is fixedly connected to the circuit tube (2), and the movable rod body (302) is fixedly connected to the orthogonal ring bracket (4). The fixed rod body (301) and the movable rod body (302) are threadedly connected.

5. A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV, as described in claim 3, is characterized in that: The elastic cord (304) has multiple loops, and each of the multiple loops is fixedly connected with an elastic buckle (305).

6. A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV, as described in claim 5, is characterized in that: The maximum stress of the multiple elastic buckles (305) varies.

7. A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV, as described in claim 3, is characterized in that: The elastic rod (7) includes a rod body (701) on which a plurality of prefabricated grooves (702) are provided.

8. A three-dimensional ultrasonic anemometer with a non-positive exchanger array that can be mounted on a UAV, as described in claim 7, is characterized in that: The depth of the plurality of prefabricated grooves (702) increases with the distance between the fixed connection end with the inner wall of the fixed chassis (6).

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