Multi-airspeed-tube testing device

Abstract

The utility model discloses a multi-airspeed-tube testing device, and the device is characterized in that a wind indicator is rotatably disposed on a pedestal, the wind indicator comprises a first connection part and an empennage, and the empennage is disposed at one end of the first connection part; the testing support is installed at the end, away from the empennage, of the first connecting part, the testing support comprises a plurality of installation parts, each testing unit is installed on one installation part, and each testing unit comprises an airspeed tube and an airspeed meter. According to the multi-airspeed-tube testing device, static pressure data and dynamic pressure data of airspeed meters of a plurality of testing units can be obtained at the same time, the influence of the difference of environment conditions at different testing moments on a testing result is reduced to the maximum extent, and the time consistency and comparability of each group of data are ensured; therefore, the data result of each group of test units is compared with the data result of the standard meteorological equipment, the airspeed tube and airspeed meter combination with accurate speed measurement and high matching degree can be quickly and accurately screened out, and the measurement accuracy and reliability of the airspeed tube and airspeed meter combination can be improved.

Description

Technical Field

[0001] This application relates to the field of pitot tube testing technology, and in particular to a multi-pitot tube testing device. Background Technology

[0002] Wind speed, a key element in meteorological observation, plays a vital role in people's daily lives, industrial and agricultural production layouts, and weather forecasting and disaster warnings. With technological advancements, wind speed measurement technology is constantly evolving, and the pitot tube and airspeed meter, as important speed measurement tools, have gradually expanded from the aviation field to the meteorological detection field. Specifically, the airspeed meter senses the static and dynamic pressures of the airflow within the pitot tube, and then calculates the wind speed based on these pressures, offering advantages such as high real-time performance and accuracy.

[0003] In practical applications, different pitot tubes vary in their airflow sensitivity, measurement range, accuracy retention, and environmental adaptability. Furthermore, the compatibility between different pitot tubes and different airspeed meters varies, leading to deviations in wind speed data measured using both pitot tubes and airspeed meters. Currently, there is a lack of effective methods for performance testing of airspeed meter and pitot tube combinations, making it difficult to guarantee the accuracy and reliability of measurement results. Utility Model Content

[0004] This application provides a multi-pitot tube testing device, which can solve the technical problem that it is difficult to perform performance testing on the combination of pitot tube and airspeed meter in meteorological detection, resulting in the inability to verify its measurement accuracy.

[0005] This application provides a multi-pitot tube testing device, which includes a base, a wind vane, a test bracket, and multiple test units. The wind vane is rotatably mounted on the base and includes a first connecting part and a tail fin, with the tail fin located at one end of the first connecting part. The test bracket is mounted on the end of the first connecting part away from the tail fin and includes multiple mounting parts. Each of the multiple test units is mounted on one of the mounting parts, and each test unit includes a pitot tube and an airspeed meter. The airspeed meter is connected to the pitot tube and is used to sense the static pressure and dynamic pressure of the airflow inside the pitot tube, and generate static pressure data and dynamic pressure data.

[0006] In some embodiments, the test bracket further includes a second connecting portion detachably mounted to the end of the first connecting portion away from the tail fin; wherein a plurality of the mounting portions surround the circumference of the second connecting portion.

[0007] In some embodiments, the test bracket further includes multiple transition sections, with adjacent mounting sections arranged at an angle, and the multiple transition sections and multiple mounting sections are alternately connected to form a cylindrical bracket body; each test unit is mounted on the outer surface of the mounting section.

[0008] In some embodiments, the pitot tube includes a front end and a rear end arranged opposite each other along its length, the pitot tubes of the plurality of test units are parallel in length, and the front ends are all arranged away from the tail fin, and the airspeed meter of each test unit is inserted into the rear end of the pitot tube.

[0009] In some embodiments, the surface of the mounting portion includes a first mounting area and a second mounting area, the airspeed tube is disposed in the first mounting area, and the airspeed meter is disposed in the second mounting area; the first mounting area is provided with a plurality of mounting holes, which penetrate the mounting portion along the thickness direction of the mounting portion.

[0010] In some embodiments, the test bracket further includes a protective cover, which is disposed corresponding to the first mounting area and the protective cover and the mounting part enclose a receiving space, in which the airspeed meter is disposed; the protective cover is detachably mounted to the mounting part.

[0011] In some embodiments, the base includes: a base housing; and a data acquisition unit disposed within the interior space of the base housing, the data acquisition unit being electrically connected to the airspeed meters of each of the test units to receive and store static pressure data and dynamic pressure data generated by the multiple airspeed meters.

[0012] In some embodiments, the multi-pitot tube testing device further includes a conductive slip ring comprising an inner cylinder and an outer cylinder, one of which is mounted on the base housing and electrically connected to the data acquisition unit, and the other is mounted on the wind vane and electrically connected to the airspeed meters of the plurality of testing units.

[0013] In some embodiments, the wind vane further includes a rotating part rotatably mounted on the base housing and having a rotating cavity facing the base housing, wherein the conductive slip ring is disposed in the rotating cavity; the first connecting part has a through wire passage communicating with the rotating cavity; wherein each of the test units further includes a connecting harness connected to the airspeed gauge, and the connecting harnesses of the plurality of test units pass through the wire passage and enter the rotating cavity to be electrically connected to the conductive slip ring.

[0014] In some embodiments, the multi-pit speed tube testing device further includes a data processing unit, which is used to receive static pressure data and dynamic pressure data transmitted by multiple airspeed meters collected by the data acquisition unit, and then calculate and compare the wind speed data of multiple testing units.

[0015] A multi-pitot tube testing device based on an embodiment of this application simultaneously acquires static and dynamic pressure data from multiple pitot tubes and pitot tubes by mounting multiple test units on a test bracket. Compared to testing different pitot tube and pitot tube combinations one by one, this effectively reduces the testing cycle. In this application, all test units perform wind speed tests within the same time period, minimizing the impact of differences in environmental conditions at different test times on the test results and ensuring the temporal consistency and comparability of each set of data. Furthermore, comparing the data results of each set of test units with the data results of standard meteorological equipment allows for the rapid and accurate selection of pitot tube and pitot tube combinations with high accuracy and matching degree, helping to improve the measurement accuracy and reliability of pitot tube and pitot tube combinations. In addition, in this application, the test bracket is installed at the end of the first connecting part away from the tail fin. By rotating the wind vane, the test bracket and the multiple test units installed on the test bracket are always facing the wind, thereby acquiring accurate wind speed data and eliminating measurement errors caused by wind direction deviation. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the structure of a multi-pitcher testing device according to an embodiment of this application;

[0018] Figure 2 This is an exploded structural diagram of a multi-pitcher testing device according to an embodiment of this application;

[0019] Figure 3 This is an exploded structural diagram of a test bracket according to an embodiment of this application;

[0020] Figure 4 This is a cross-sectional schematic diagram of a multi-pitcher testing device according to an embodiment of this application;

[0021] Figure 5 for Figure 4 A magnified view of a portion of point A in the middle;

[0022] Figure label:

[0023] 1. Multi-pitcher testing device;

[0024] 10. Base; 20. Wind vane; 30. Test bracket; 40. Test unit; 50. Conductive slip ring;

[0025] 11. Base housing; 12. Rotating shaft; 21. First connecting part; 22. Tail fin; 23. Rotating part; 31. Mounting part; 32. Second connecting part; 33. Protective cover; 34. Transition part; 41. Pitot tube; 42. Pitot gauge;

[0026] 210. Cable passage; 230. Rotating cavity; 310. Mounting hole; 311. First mounting area; 312. Second mounting area. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0028] With continuous innovation in wind speed measurement technology, pitot tubes and airspeed meters, as important speed measurement tools, have gradually expanded from the aviation field to the meteorological field. Typically, the airspeed meter is placed at the end of the pitot tube. The pitot tube and airspeed meter are used to determine the static and dynamic pressure of the airflow, and then the data is converted based on Bernoulli's equation to determine the wind speed. In practical applications, the performance of different pitot tubes varies, and the compatibility between different pitot tubes and airspeed meters differs, leading to deviations in the measured wind speed data.

[0029] In the aviation field, wind tunnel testing of actual aircraft systems is typically used to verify the performance of pitot tubes and airspeed meters. However, environmental factors are constantly changing in meteorological monitoring, and wind tunnel testing cannot simulate the dynamically changing environment in meteorological monitoring, nor can it verify the performance of different pitot tube and airspeed meter combinations under dynamically changing conditions, thus presenting certain limitations. Therefore, how to select appropriate pitot tubes, airspeed meters, and combinations of pitot tubes and airspeed meters to ensure the accuracy and reliability of measurement results has become a pressing technical challenge for the application of pitot tubes and airspeed meters in meteorological monitoring.

[0030] To address the aforementioned problems in related technologies, this application proposes a multi-pitcher testing device. Please refer to [link to relevant documentation]. Figure 1 The multi-pitcher test device 1 includes a base 10, a wind vane 20, a test bracket 30, a test unit 40, and a data processing unit.

[0031] Please participate Figures 1-2 , Figure 2This is an exploded structural diagram of a multi-pitcher testing device 1 according to an embodiment of this application. A wind vane 20 is rotatably mounted on a base 10. The wind vane 20 includes a first connecting portion 21 and a tail fin 22. The tail fin 22 is located at one end of the first connecting portion 21. A test bracket 30 is mounted at the end of the first connecting portion 21 away from the tail fin 22. The test bracket 30 includes multiple mounting portions 31, and each test unit 40 is mounted on one mounting portion 31. Thus, in complex and changeable meteorological environments, the rotation of the wind vane 20 allows the test unit 40 to directly face the oncoming wind, thereby obtaining the most accurate data, eliminating measurement errors caused by wind direction deviation, and improving overall measurement accuracy.

[0032] Each test unit 40 includes an airspeed tube 41 and an airspeed meter 42. The airspeed meter 42 is connected to the airspeed tube 41 and is used to sense the static and dynamic pressure of the airflow inside the airspeed tube 41, generating static and dynamic pressure data. This application, by simultaneously mounting multiple test units 40 on the test bracket 30, simultaneously acquires static and dynamic pressure data from multiple airspeed meters 42, effectively reducing the test cycle compared to testing one by one. All test units 40 are tested for wind speed in the same environment and at the same time, minimizing the impact of differences in environmental conditions at different test times on the test results, ensuring the temporal consistency and comparability of each set of data. By comparing the data results of each set of test units with the data results of standard meteorological equipment, the combination of airspeed tube 41 and airspeed meter 42 with good performance can be effectively selected.

[0033] In one embodiment of this application, the base 10 includes a base housing 11 and a data acquisition unit. The data acquisition unit is located in the internal space of the base housing 11. The data acquisition unit is used to electrically connect with the airspeed meter 42 of each test unit 40. In a specific implementation, the base 10, wind vane 20, test bracket 30 and test unit 40 are all placed in the test position in an outdoor environment. The data acquisition unit supplies power to the airspeed meter 42 of each test unit 40. The airspeed meter 42 transmits the sensed static pressure data and dynamic pressure data to the data acquisition unit. The data acquisition unit stores the received data for subsequent data processing and comparative analysis.

[0034] In one embodiment of this application, the data processing unit can interact with the data acquisition unit to receive static and dynamic pressure data transmitted by multiple airspeed meters 42 collected by the data acquisition unit, and determine the wind speed data of each test unit 40 based on the static and dynamic pressure data. In a specific implementation, after the base 10, wind vane 20, test bracket 30, and test unit 40 have completed testing in an outdoor environment, the data acquisition unit in the base 10 is connected to the data processing unit to achieve communication between the data processing unit and the data acquisition unit, and to complete data interaction.

[0035] It should be noted that the data processing unit can also connect to meteorological monitoring equipment to obtain standard wind speed data at the test location during the same period. The windward wind speed data measured by each test unit 40 is compared with the standard wind speed data to determine the measurement error of each test unit 40, thus determining the accurate combination of the pitot tube and airspeed meter. Furthermore, the multi-pitot tube testing device 1 of this application can acquire and compare windward wind speed data of each test unit 40 under different environmental conditions and over long periods, reflecting not only the accuracy of the pitot tube and airspeed meter under different environmental conditions but also their operational stability.

[0036] In this embodiment, the pitot tube 41 includes a front end and a rear end arranged opposite each other along its length. The pitot tubes 41 of multiple test units 40 are parallel in length, and the multiple pitot tubes 41 receive the impact of the airflow at the same angle, avoiding the introduction of additional measurement errors. The front ends of the pitot tubes 41 are all positioned away from the tail fin 22, so that the rotation of the wind vane 20 ensures that the front ends of the pitot tubes 41 always directly face the oncoming wind, enabling the airspeed meter 42 to more accurately sense the impact of the airflow and obtain accurate dynamic pressure data. In specific implementations, the types of pitot tubes 41 include, but are not limited to, S-type pitot tubes and L-type pitot tubes.

[0037] Furthermore, the airspeed indicator 42 is connected to the tail end of the airspeed tube 41. Generally, the airspeed indicator 42 is connected to the airspeed tube 41 via an air tube. The airspeed tube 41 has a total pressure tube and a static pressure tube. The airspeed indicator 42 senses the effect of the airflow through the total pressure tube, that is, it measures the dynamic pressure data of the airflow. The airspeed indicator 42 senses the effect of the static air pressure through the static pressure tube, that is, it measures the static pressure data of the airflow. Then, the data processing unit calculates the wind speed data based on the difference between the dynamic pressure data and the static pressure data.

[0038] Please see Figure 3 , Figure 3 This is an exploded structural diagram of a test bracket 30 according to an embodiment of this application. In one embodiment, the test bracket 30 further includes a second connecting portion 32, which is detachably mounted on the end of the first connecting portion 21 away from the tail fin 22. A plurality of mounting portions 31 are arranged around the circumference of the second connecting portion 32. The plurality of mounting portions 31 are evenly distributed around the circumference of the second connecting portion 32, which helps to reduce measurement errors caused by the positional distribution of each test unit 40.

[0039] Understandably, the test bracket 30 and tail fin 22 are located at both ends of the first connecting part 21. Considering gravity balance, the test bracket 30 can be detachably installed on the wind vane 20 to facilitate matching and replacement of the wind vane 20 according to the overall weight of the multiple test units 40. When there are many test units 40 and they are heavy, a larger and heavier wind vane 20 with tail fin 22 should be used. When there are few test units 40 and they are light, a smaller and lighter wind vane 20 with tail fin 22 can be used. This flexible adjustment of the center of gravity of the wind vane 20, test bracket 30, and the overall structure of the test unit 40 prevents the multi-pitot tube test device 1 from tipping over due to an unstable center of gravity.

[0040] Optionally, the end of the first connecting part 21 away from the tail fin 22 has a plug-in end, and the second connecting part 32 has a plug-in hole facing the first connecting part 21. The plug-in end is inserted into the plug-in hole in a horizontal direction and fixed to the plug-in hole by fasteners to ensure the connection stability between the wind vane 20 and the test bracket 30 and reduce the risk of the test bracket 30 detaching from the wind vane 20 due to factors such as excessive wind speed. The fasteners can be screws or bolts.

[0041] Furthermore, both the first connecting portion 21 and the second connecting portion 32 are provided with mounting holes extending in the horizontal direction. After the insertion end is inserted into the insertion hole, the fastener locks the first connecting portion 21 and the second connecting portion 32 in the horizontal direction. The installation direction of the fastener is the same as the insertion direction of the first connecting portion 21 and the second connecting portion 32. The first connecting portion 21 and the second connecting portion 32 can be locked by the fastener at different insertion depths, which is more conducive to adjusting the relative position of the test bracket 30 and the wind vane 20 to balance the center of gravity.

[0042] Optionally, the end of the first connecting part 21 away from the tail fin 22 is threaded to the second connecting part 32, and the first connecting part 21 and the second connecting part 32 are easily and conveniently connected together by screwing.

[0043] Please continue reading. Figure 5 The surface of the mounting portion 31 includes a first mounting area 311 and a second mounting area 312. The first mounting area 311 has multiple mounting holes 310 that penetrate the mounting portion 31 along its thickness direction. The pitot tube 41 is mounted in the first mounting area 311 through the multiple mounting holes 310. In a specific implementation, some pitot tubes 41 are equipped with a loading base, which is locked to the mounting holes 310 by screws. Optionally, the pitot tube 41 can also be fixed by cable ties, which pass through the multiple mounting holes 310 and mount the pitot tube 41 in the first mounting area 311. The airspeed indicator 42 is located in the second mounting area 312, which has a mounting surface. The airspeed indicator 42 can be bonded to the mounting surface by adhesive.

[0044] In this embodiment, the test bracket 30 further includes a protective cover 33, which is disposed corresponding to the first mounting area 311. The protective cover 33 and the mounting part 31 enclose a receiving space, in which the airspeed meter 42 is disposed. The protective cover 33 is detachably installed on the mounting part 31. After the airspeed meter 42 is connected to the second mounting area 312, the protective cover 33 is installed on the mounting part 31 to shield the airspeed meter 42 and prevent rainwater, dew, and other liquids in the outdoor environment from entering the airspeed meter 4 and damaging its circuitry.

[0045] Specifically, the protective cover 33 is snap-fitted to the mounting portion 31. The mounting portion 31 also includes snap-fit ​​grooves located around the second mounting area 312. The protective cover 33 includes a top wall and multiple side walls connected to the periphery of the top wall. The top wall is positioned opposite to the second mounting area 312. A snap-fit ​​end is provided on the side of the side wall away from the top wall. After the snap-fit ​​end snaps into the snap-fit ​​groove, the protective cover 33 and the second mounting area 312 are enclosed to form an accommodating space. At least one side wall of the protective cover 33 has a wiring hole to allow the piping and wiring of the airspeed meter 42 to pass through. To ensure the airtightness of the accommodating space, after the protective cover 33 is installed, the connection between the protective cover 33 and the mounting portion 31, as well as the wiring hole, must be sealed with sealant. The sealant can be an organosilicon sealant.

[0046] In one embodiment of this application, the test bracket 30 further includes multiple transition portions 34, with adjacent mounting portions 31 arranged at an angle, and the multiple transition portions 34 and multiple mounting portions 31 alternately connected to form a cylindrical bracket body, with each test unit 40 mounted on the outer surface of the mounting portion. The transition portions 34 are provided with multiple counterweight openings, which penetrate the transition portion 34 along its thickness direction. Providing counterweight openings and mounting holes 310 not only reduces the weight of the test bracket 30 but also balances the internal and external air pressure of the cylindrical bracket body, preventing excessive pressure differences between the inside and outside of the cylindrical bracket body from affecting wind speed measurement.

[0047] In the Wind Vane 20, the shape of the tail fin 22 is not limited to... Figures 1-2 The quadrilateral structure shown allows technicians to adjust the size and shape of the tail fin 22 according to the center of gravity and rotational wind power requirements. The wind vane 20 also includes a rotating part 23, which is connected to the central region of the first connecting part 21 and located between the test bracket 30 and the tail fin 22. The rotating part 23 is rotatably mounted on the base housing 11. After multiple test units 40 are mounted on the test bracket 30 and the test bracket 30 is mounted on the wind vane 20, the wind vane 20 can rotate freely around the rotation axis of the rotating part 23.

[0048] In this embodiment, the airspeed gauges 42 of the multiple test units 40 need to be connected to the data acquisition unit via wiring to achieve electrical connection. To prevent the wiring from becoming tangled due to the rotation of the wind vane 20, the multi-pitot tube testing device 1 further includes a conductive slip ring 50. The conductive slip ring 50 includes an inner cylinder and an outer cylinder, which are electrically connected. One of the inner and outer cylinders is mounted on the base housing 11 and electrically connected to the data acquisition unit, while the other is mounted on the wind vane 20 and electrically connected to the airspeed gauges 42 of the multiple test units 40. In this way, a stable and reliable rotational communication structure is formed between the data acquisition unit, the conductive slip ring 50, and the airspeed gauges 42 of each test unit 40. When each test unit 40 rotates with the wind vane 20, the conductive slip ring 50 can ensure that the electrical connection and data transmission between the test unit 40 and the data acquisition unit are not affected.

[0049] Each test unit 40 also includes a connecting harness connected to the airspeed indicator 42, the connecting harness being used for electrical connection to the data acquisition unit. For example... Figures 4-5 As shown, Figure 4 This is a cross-sectional schematic diagram of a multi-pitcher testing device 1 according to an embodiment of this application. Figure 5 for Figure 4 The enlarged view at point A shows that the first connecting part 21 and the rotating part 23 of the weather vane 20 have a hollow structure. The first connecting part 21 is provided with a through wire passage 210, which connects to the internal space of the first connecting part 21. The design of the wire passage 210 allows the connecting wires to pass through the inside of the weather vane 20, which helps to reduce the interference and damage of the external environment to the connecting wires.

[0050] Furthermore, the rotating part 23 has a rotating cavity 230 facing the base housing 11, and a conductive slip ring 50 is disposed in the rotating cavity 230. The wire passage 210 is connected to the rotating cavity 230, and the connecting wires of the multiple test units 40 pass through the wire passage 210 and enter the rotating cavity 230 to be electrically connected to the conductive slip ring 50. In this way, the multiple test units 40 can rotate freely with the wind vane 20, while effectively preventing the connecting wires of the multiple test units 40 from getting tangled.

[0051] As a feasible implementation, the base 10 also includes a rotating shaft 12 disposed on the outer wall of the base housing 11. The inner cylinder of the conductive slip ring 50 is mounted on the rotating shaft 12, and the outer cylinder is mounted on the rotating cavity 230 of the rotating part 23. In the direction of extension of the rotating axis, the inner cylinder of the conductive slip ring 50 extends at least partially out of its outer cylinder and is mounted on the inner wall of the rotating cavity 230 by a bearing. In this way, the rotating part 23 can rotate freely relative to the rotating shaft 12.

[0052] In the accompanying drawings of this embodiment, the same or similar reference numerals correspond to the same or similar components. In the description of this application, it should be understood that if terms such as "upper," "lower," "left," and "right" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, they are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the terms used to describe positional relationships in the accompanying drawings are only for illustrative purposes and should not be construed as limiting this patent. For those skilled in the art, the specific meaning of the above terms can be understood according to the specific circumstances.

[0053] The above are merely preferred embodiments of this application and are not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A multi-pitcher testing device, characterized in that, include: Base; A wind vane is rotatably mounted on the base. The wind vane includes a first connecting part and a tail fin, with the tail fin located at one end of the first connecting part. A test bracket is installed at the end of the first connecting portion away from the tail fin; the test bracket includes multiple mounting portions. Multiple test units are provided, each of which is installed in one of the mounting units. Each test unit includes an airspeed tube and an airspeed meter. The airspeed meter is connected to the airspeed tube and is used to sense the static pressure and dynamic pressure of the airflow inside the airspeed tube, and to generate static pressure data and dynamic pressure data.

2. The multi-pitcher testing device according to claim 1, characterized in that, The test bracket further includes a second connecting part, which is detachably mounted on the end of the first connecting part away from the tail fin; The plurality of mounting portions are arranged around the circumference of the second connecting portion.

3. The multi-pitcher testing device according to claim 1, characterized in that, The test bracket also includes multiple transition sections, with two adjacent mounting sections arranged at an angle, and the multiple transition sections and multiple mounting sections are alternately connected to form a cylindrical bracket body; Each of the test units is mounted on the outer surface of the mounting portion.

4. The multi-pitcher testing device according to claim 1, characterized in that, The pitot tube includes a front end and a rear end that are arranged opposite each other along its length. The pitot tubes of the plurality of test units are parallel in length, and the front ends are all arranged away from the tail fin. The airspeed meter of each test unit is inserted into the rear end of the pitot tube.

5. The multi-pitcher testing device according to claim 4, characterized in that, The surface of the mounting part includes a first mounting area and a second mounting area, the airspeed tube is disposed in the first mounting area, and the airspeed meter is disposed in the second mounting area; The first mounting area is provided with a plurality of mounting holes, which penetrate the mounting portion along the thickness direction of the mounting portion.

6. The multi-pitcher testing device according to claim 5, characterized in that, The test bracket also includes a protective cover, which is provided corresponding to the first installation area, and the protective cover and the installation part enclose a receiving space, in which the airspeed meter is located; The protective cover is detachably installed on the mounting part.

7. The multi-pitcher testing device according to claim 1, characterized in that, The base includes: Base shell; and A data acquisition unit is located inside the base housing. The data acquisition unit is electrically connected to the airspeed meters of each of the test units to receive and store static pressure data and dynamic pressure data generated by multiple airspeed meters.

8. The multi-pitcher testing device according to claim 7, characterized in that, The multi-pitot tube testing device also includes a conductive slip ring, which comprises an inner cylinder and an outer cylinder. One of the inner cylinder and the outer cylinder is installed on the base housing and electrically connected to the data acquisition unit, and the other is installed on the wind vane and electrically connected to the airspeed meters of the multiple testing units.

9. The multi-pitcher testing device according to claim 8, characterized in that, The wind vane also includes a rotating part, which is rotatably mounted on the base housing and has a rotating cavity facing the base housing, and the conductive slip ring is disposed in the rotating cavity; The first connecting part is provided with a through wire passage, which is connected to the rotating cavity; Each of the test units further includes a connecting harness connected to the airspeed gauge. The connecting harnesses of the multiple test units pass through the wire passage and enter the rotating cavity to be electrically connected to the conductive slip ring.

10. The multi-pitcher testing device according to claim 7, characterized in that, The multi-pit speed tube testing device also includes a data processing unit, which is used to receive static pressure data and dynamic pressure data transmitted by multiple airspeed meters collected by the data acquisition unit, and then calculate and compare the wind speed data of multiple testing units.

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