Miniature dynamic porous probe as well as calibration method and use method thereof

Abstract

The invention discloses a miniature dynamic porous probe and a calibration method and a using method thereof.The probe comprises a probe body, the probe body is arranged in a measured flow field, and the probe body comprises a pressure measuring part; the pressure measuring part is provided with a first pressure measuring hole, a second pressure measuring hole, a third pressure measuring hole, a fourth pressure measuring hole and a fifth pressure measuring hole, the probe is provided with a sixth pressure measuring hole, and the first pressure measuring hole and the third pressure measuring hole extend to the two sides of the first differential pressure sensor respectively. The fourth pressure measuring hole and the fifth pressure measuring hole extend to the two sides of the second differential pressure sensor respectively, the second pressure measuring hole extends to the first pulsating pressure sensor, and the sixth pressure measuring hole extends to the second pulsating pressure sensor. According to the scheme, the number of the sensors is reduced, so that the size of the head of the probe is reduced, the spatial resolution of the probe is improved, and disturbance to a flow field is also reduced.

Description

Technical Field

[0001] This application relates to the field of experimental measurement technology, and in particular to a miniature dynamic porous probe. Background Technology

[0002] Compressors and turbines, or other turbomachinery, convert the internal energy of a gas into mechanical energy through the high-speed rotation of blades. Due to this high-speed rotation, the internal flow field of turbomachinery exhibits strong unsteadiness. Unsteady effects arise from phenomena such as blade wake sweeping, flow interference between moving and stationary blades, interstage matching, and rotational stall. To obtain the internal flow field structure of a compressor or turbine and to provide feedback for design improvements, it is necessary to use probes to dynamically measure the internal flow field.

[0003] Taking a heavy-duty gas turbine compressor as an example, with a compressor speed of 3000 r / min and 87 blades in a certain stage, the blade passage frequency in a fixed coordinate system can reach 4.4 kHz. According to the Nyquist sampling theorem, to obtain detailed flow field information, a high-frequency response measurement should be performed at least twice the physical signal frequency. In practical applications, to obtain the unsteady characteristics and flow field in each blade passage, a multiple of 10 is usually required, meaning there are 10 sampling points in each blade passage, and the probe measurement frequency needs to be reduced to 44 kHz. This places high demands on the probe's response frequency.

[0004] Because contact measurement methods using probes can disturb the flow field, thus affecting the accuracy of the measurement results, from a probe design perspective, it is necessary to minimize the size of the probe to improve its spatial resolution.

[0005] Existing technology CN107101798B discloses a dynamic five-hole probe, including a pressure sensing part, a pressure measuring hole transition section, a pressure acquisition section, a dynamic pressure sensor, and a flexible-walled pressure-reducing tube. The pressure sensing part is provided with pressure measuring holes to sense the three-dimensional dynamic pressure components of the measured airflow. The pressure measuring hole transition section transitions the five-hole structure at the inlet end face to the five-hole structure at the outlet end face. The pressure acquisition section has a centrally symmetrical pressure measuring hole structure with the same cross-section as the outlet of the transition section, as well as pressure sensor mounting holes, which are connected to the five pressure measuring holes. The dynamic pressure sensors are installed in the sensor mounting holes to measure the dynamic pressure of the airflow. The flexible-walled pressure-reducing tube is used to reduce the cavity effect. Because the pressure sensor is far from the pressure measuring hole at the probe head, the pressure attenuates significantly in the pressure-reducing tube. The transfer function of the pressure-reducing tube needs to be calibrated before use, thus increasing the measurement uncertainty of the probe.

[0006] Existing technology CN119738586A discloses a five-hole probe-type pitot tube, comprising: an exhaust port on the side wall of a middle tube; a head connector with one end hemispherical and the other end connected to the head end of the middle tube; a first through hole at the apex of the hemispherical part; four second through holes evenly distributed around the first through hole; a tail connector connected to the tail section of the middle tube; the tail connector and head connector respectively blocking both ends of the middle tube to form a cavity structure; first connecting pipes axially inserted inside the middle tube; the heads of the five first connecting pipes respectively connected to the first and second through holes; the tail ends of the five first connecting pipes exposed through the tail connector; and the heads of the second connecting pipes communicating with the cavity structure through the tail connector. This solution is suitable for aerodynamic measurements in open external flow spaces and cannot meet the needs of complex flow measurements inside a compressor.

[0007] In summary, neither of the two existing technologies can accurately measure the complex flow inside the compressor, increasing the measurement uncertainty of the probe. Summary of the Invention

[0008] The purpose of this application is to solve the aforementioned technical problems.

[0009] To achieve the above objectives, the first aspect of this application proposes a miniature dynamic multi-hole probe, comprising a probe placed in the flow field to be measured. The probe includes a pressure measuring section, which is provided with a first pressure measuring hole, a second pressure measuring hole, a third pressure measuring hole, a fourth pressure measuring hole, and a fifth pressure measuring hole. The probe is provided with a sixth pressure measuring hole. The first and third pressure measuring holes extend to both sides of a first differential pressure sensor, the fourth and fifth pressure measuring holes extend to both sides of a second differential pressure sensor, the second pressure measuring hole extends to a first pulsating pressure sensor, and the sixth pressure measuring hole extends to the second pulsating pressure sensor.

[0010] Furthermore, the pressure measuring part is hemispherical, and the second pressure measuring hole is disposed at the top axial end of the hemispherical surface of the pressure measuring part. The first pressure measuring hole, the third pressure measuring hole, the fourth pressure measuring hole and the fifth pressure measuring hole are located on the hemispherical surface of the pressure measuring part and are evenly distributed circumferentially with the second pressure measuring hole as the center.

[0011] Furthermore, the angle between the first pressure measuring hole and the axis of the probe is 30°~35°, the angle between the fourth pressure measuring hole and the axis of the probe is 40°~45°, and the extension length of the second pressure measuring hole is 1~2mm.

[0012] Furthermore, the sixth pressure measuring hole is disposed on the side of the probe and located outside the pressure measuring part, and the sixth pressure measuring hole extends radially inward along the probe with an extension length of 1~2mm.

[0013] Furthermore, the diameters of the first pressure measuring hole, the second pressure measuring hole, the third pressure measuring hole, the fourth pressure measuring hole, the fifth pressure measuring hole, and the sixth pressure measuring hole are all 0.4~0.6mm.

[0014] Furthermore, the miniature dynamic porous probe also includes a support rod connected to the end of the probe away from the pressure measuring part.

[0015] To achieve the above objectives, a second aspect of this application proposes a calibration method for a miniature dynamic porous probe, using the miniature dynamic porous probe as described above, the method comprising the following steps: The micro dynamic porous probe was used to measure the physical parameters under different working conditions in a wind tunnel, and the calibration fitting relationship between the aerodynamic coefficient and the measured physical parameters was obtained through data fitting.

[0016] Furthermore, the measured physical parameters include Mach number, yaw angle, and pitch angle, and the aerodynamic coefficients include yaw angle coefficient, pitch angle coefficient, total pressure coefficient, and static pressure coefficient.

[0017] Furthermore, the micro dynamic porous probe is used for calibration in a wind tunnel, controlling the Mach number, yaw angle, and pitch angle to vary within the operating range, to obtain the calibration fitting relationship between the aerodynamic coefficient and the measured physical parameter within the calibration range. The calibration range includes a Mach number of 0.2 to 0.8, a yaw angle of -30° to +30°, and a pitch angle of -20° to +20°.

[0018] Furthermore, the obtained calibration fitting relationships include a first fitting relationship, a second fitting relationship, a third fitting relationship, and a fourth fitting relationship, which are as follows: in, This is the yaw angle coefficient; This is the pitch angle coefficient; This is the total pressure coefficient; This is the static pressure coefficient; The pressure gauge is located at the center hole. The pressure difference between the left and right orifices; The pressure difference between the upper and lower holes; Quasi-static pressure; Total pressure; It is static pressure; It is the Mach number; Yaw angle; It is the pitch angle.

[0019] To achieve the above objectives, a third aspect of this application proposes a method for using a miniature dynamic porous probe, employing the miniature dynamic porous probe as described above, the method comprising the following steps: The pressure difference between the left and right holes, the pressure difference between the upper and lower holes, the gauge pressure of the center hole, and the quasi-static pressure were measured using the aforementioned micro dynamic multi-hole probe. Based on the pressure difference between the left and right holes, the pressure difference between the upper and lower holes, the gauge pressure of the center hole, and the quasi-static pressure, the yaw angle coefficient and the pitch angle coefficient are obtained. Based on the selected first Mach number, a first fitting relationship is obtained between the yaw angle coefficient and the yaw angle and pitch angle. Based on the selected first Mach number, a second fitting relationship is obtained between the pitch angle coefficient and the yaw angle and pitch angle. The yaw angle and pitch angle are obtained based on the first and second fitting relationships; The total pressure coefficient and static pressure coefficient are obtained based on the third and fourth fitting relationships; The total pressure and static pressure are obtained based on the total pressure coefficient and static pressure coefficient; The second Mach number is obtained based on total pressure and static pressure; If the residual between the first Mach number and the second Mach number is greater than or equal to the residual threshold, then the first fitting relationship and the second fitting coefficient are obtained based on the second Mach number, and the relevant parameters are recalculated until the residual is less than the residual threshold.

[0020] Furthermore, the first fitting relationship, the second fitting relationship, the third fitting relationship, and the fourth fitting relationship are as follows: in, This is the yaw angle coefficient; This is the pitch angle coefficient; This is the total pressure coefficient; This is the static pressure coefficient; The pressure gauge is located at the center hole. The pressure difference between the left and right orifices; The pressure difference between the upper and lower holes; Quasi-static pressure; Total pressure; It is static pressure; It is the Mach number; Yaw angle; It is the pitch angle.

[0021] Furthermore, the process of obtaining the second Mach number based on total pressure and static pressure includes solving for the second Mach number based on the total pressure and static pressure according to the isentropic process parameter relationship, wherein the isentropic process parameter relationship is as follows: in, It is the second Mach number; Total pressure; It is static pressure; It represents the adiabatic index.

[0022] Furthermore, the residual threshold is 0.01.

[0023] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. This solution achieves the functionality of two sensors in the prior art by using only one differential pressure sensor through probe head configuration design, thereby reducing the number of sensors, reducing the probe head size, improving the probe's spatial resolution, and reducing disturbance to the flow field. 2. This scheme directly mounts the sensor on the probe head, resulting in a very small cavity and negligible lumen effect. This improves the dynamic response frequency of the probe and avoids the tedious work and measurement uncertainty caused by probe transfer function calibration. 3. This scheme uses a single differential pressure sensor to directly measure the pressure difference between the left and right holes and the top and bottom holes. Compared with the traditional five-hole probe method of using two pressure sensors to measure the pressure of the left and right or top and bottom holes separately and then calculating the difference, it reduces the measurement uncertainty. 4. Based on the probe head configuration, this scheme constructs new probe calibration coefficients and calculates aerodynamic parameters such as total pressure and static pressure, thereby improving measurement accuracy.

[0024] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0025] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 A schematic diagram of a three-dimensional model of a micro dynamic porous probe in one embodiment is shown; Figure 2 A schematic diagram of a front view of a miniature dynamic porous probe in one embodiment is shown; Figure 3 A schematic diagram of a side view of a miniature dynamic porous probe in one embodiment is shown; Figure 4 A schematic top view of a miniature dynamic porous probe in one embodiment is shown.

[0026] Reference numerals: 1. First pressure measuring hole; 2. Second pressure measuring hole; 3. Third pressure measuring hole; 4. Fourth pressure measuring hole; 5. Fifth pressure measuring hole; 6. Sixth pressure measuring hole; 7. First differential pressure sensor; 8. Second differential pressure sensor; 9. First pulsating pressure sensor; 10. Second pulsating pressure sensor. Detailed Implementation

[0027] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0028] The present invention will be further described in detail below with reference to specific embodiments, which should not be construed as limiting the scope of protection claimed by the present invention.

[0029] Example 1 According to one aspect of the present invention, a miniature dynamic porous probe is proposed, such as... Figure 1 As shown, the device includes a probe placed in the flow field to be measured. The probe includes a pressure measuring part, which is provided with a first pressure measuring hole 1, a second pressure measuring hole 2, a third pressure measuring hole 3, a fourth pressure measuring hole 4, and a fifth pressure measuring hole 5. The probe is provided with a sixth pressure measuring hole 6. The first pressure measuring hole 1 and the third pressure measuring hole 3 extend to both sides of the first differential pressure sensor 7, the fourth pressure measuring hole 4 and the fifth pressure measuring hole 5 extend to both sides of the second differential pressure sensor 8, the second pressure measuring hole 2 extends to the first pulsating pressure sensor 9, and the sixth pressure measuring hole 6 extends to the second pulsating pressure sensor 10.

[0030] Specifically, in this embodiment, the basic configuration of the micro dynamic porous probe is L-shaped, with the probe extending into the flow field from the channel wall.

[0031] Furthermore, such as Figure 2 As shown, the pressure measuring part is hemispherical, and the second pressure measuring hole 2 is located at the top of the hemispherical surface of the pressure measuring part along the axial direction. The first pressure measuring hole 1, the third pressure measuring hole 3, the fourth pressure measuring hole 4 and the fifth pressure measuring hole 5 are located on the hemispherical surface of the pressure measuring part and are evenly distributed circumferentially with the second pressure measuring hole 2 as the center.

[0032] Furthermore, such as Figure 3 and Figure 4As shown, the angle between the first pressure measuring hole 1 and the axis of the probe is 30°~35°, the angle between the fourth pressure measuring hole 4 and the axis of the probe is 40°~45°, and the extension length of the second pressure measuring hole 2 is 1~2mm.

[0033] By mounting the sensor directly on the probe head and minimizing the distance between the sensor and the pressure port, the pressure signal attenuation is negligible, and there is no need to calibrate the transfer function.

[0034] Furthermore, the sixth pressure measuring hole 6 is located on the side of the probe and outside the pressure measuring part. The sixth pressure measuring hole 6 extends radially inward along the probe, with an extension length of 1~2mm.

[0035] Specifically, in this embodiment, a sixth pressure measuring hole 6 with a diameter of 0.5 mm is arranged directly above the probe support on the upper side of the probe to draw pressure to the second pulsating pressure sensor 10 to measure the local static pressure.

[0036] The sixth pressure measuring port is located near the fifth port on the head. Through the flow guide of the probe head, the sixth pressure measuring port can obtain static pressure close to that at the head position, which is used for subsequent calibration and calculation.

[0037] The problem of missing static pressure parameters caused by directly measuring differential pressure using a differential pressure sensor is solved by utilizing a separate sixth pressure measurement port on the probe head.

[0038] Furthermore, the diameters of the first pressure measuring hole 1, the second pressure measuring hole 2, the third pressure measuring hole 3, the fourth pressure measuring hole 4, the fifth pressure measuring hole 5, and the sixth pressure measuring hole 6 are all 0.4~0.6mm.

[0039] Furthermore, the miniature dynamic porous probe also includes a support rod connected to the end of the probe furthest from the pressure measuring part.

[0040] Example 2 According to another aspect of the present invention, a calibration method for a micro dynamic porous probe is proposed, using the micro dynamic porous probe as described above, the calibration method comprising the following steps: A miniature dynamic porous probe was used to measure the physical parameters under different operating conditions in a wind tunnel. The calibration fitting relationship between the aerodynamic coefficient and the measured physical parameters was obtained through data fitting.

[0041] Furthermore, the measured physical parameters include Mach number, yaw angle, and pitch angle, and the aerodynamic coefficients include yaw angle coefficient, pitch angle coefficient, total pressure coefficient, and static pressure coefficient.

[0042] Furthermore, a miniature dynamic porous probe was used to perform calibration in a wind tunnel, controlling the variation of Mach number, yaw angle, and pitch angle within the operating range, to obtain the calibration fitting relationship between the aerodynamic coefficient and the measured physical parameter within the calibration range. The calibration range includes Mach number of 0.2~0.8, yaw angle of -30°~+30°, and pitch angle of -20°~+20°.

[0043] Furthermore, the obtained calibration fitting relationships include a first fitting relationship, a second fitting relationship, a third fitting relationship, and a fourth fitting relationship, which are as follows: in, This is the yaw angle coefficient; This is the pitch angle coefficient; This is the total pressure coefficient; This is the static pressure coefficient; The pressure gauge is located at the center hole. The pressure difference between the left and right orifices; The pressure difference between the upper and lower holes; Quasi-static pressure; Total pressure; It is static pressure; It is the Mach number; Yaw angle; It is the pitch angle.

[0044] Example 3 According to another aspect of the present invention, a method for using a micro dynamic porous probe is provided, using the micro dynamic porous probe as described above, the method comprising the following steps: S1. The pressure difference between the left and right holes, the pressure difference between the upper and lower holes, the gauge pressure of the center hole, and the quasi-static pressure are measured using the micro dynamic multi-hole probe.

[0045] S2. Based on the pressure difference between the left and right holes, the pressure difference between the upper and lower holes, the gauge pressure of the center hole, and the quasi-static pressure, the yaw angle coefficient and the pitch angle coefficient are obtained.

[0046] Specifically, in this embodiment, the yaw angle coefficient and pitch angle coefficient are calculated based on the left and right hole pressure difference, the upper and lower hole pressure difference, the center hole gauge pressure, and the quasi-static pressure, according to the definitions of yaw angle coefficient and pitch angle coefficient.

[0047] S3. Based on the selected first Mach number, obtain the first fitting relationship between the yaw angle coefficient and the yaw angle and pitch angle, and based on the selected first Mach number, obtain the second fitting relationship between the pitch angle coefficient and the yaw angle and pitch angle.

[0048] Specifically, in this embodiment, it is assumed that Ma = Ma1 (initial value), Ma1 is the first Mach number, and the first fitting coefficient, the second fitting coefficient, the third fitting coefficient and the fourth fitting coefficient are obtained.

[0049] Furthermore, the first fitting relation, the second fitting relation, the third fitting relation, and the fourth fitting relation are as follows: in, This is the yaw angle coefficient; This is the pitch angle coefficient; This is the total pressure coefficient; This is the static pressure coefficient; The pressure gauge is located at the center hole. The pressure difference between the left and right orifices; The pressure difference between the upper and lower holes; Quasi-static pressure; Total pressure; It is static pressure; It is the Mach number; Yaw angle; It is the pitch angle.

[0050] S4. Based on the first fitting relationship and the second fitting relationship, obtain the yaw angle and pitch angle.

[0051] Specifically, in this embodiment, the system of equations is solved. This yields the yaw and pitch angles.

[0052] S5. The total pressure coefficient and static pressure coefficient are obtained based on the third and fourth fitting relationships.

[0053] S6. Obtain the total pressure and static pressure based on the total pressure coefficient and static pressure coefficient.

[0054] S7. The second Mach number is obtained based on the total pressure and static pressure.

[0055] Furthermore, based on the isentropic process parameter relationship, the second Mach number is obtained by solving for the total pressure and static pressure. The isentropic process parameter relationship is as follows: in, It is the second Mach number; Total pressure; It is static pressure; It represents the adiabatic index.

[0056] S8. If the residual between the first Mach number and the second Mach number is greater than or equal to the residual threshold, then the first fitting relationship and the second fitting coefficient are obtained based on the second Mach number, and the relevant parameters are recalculated until the residual is less than the residual threshold.

[0057] Furthermore, the residual threshold is 0.01.

[0058] Specifically, in this embodiment, the residual is calculated. ,like If the result is positive, the calculation converges; otherwise, start from step S3 and substitute... Recalculate the relevant parameters until convergence.

[0059] By applying the above-described technical solution of the present invention, at least the following technical effects are achieved: 1. This solution achieves the functionality of two sensors in the prior art by using only one differential pressure sensor through probe head configuration design, thereby reducing the number of sensors, reducing the probe head size, improving the probe's spatial resolution, and reducing disturbance to the flow field. 2. This scheme directly mounts the sensor on the probe head, resulting in a very small cavity and negligible lumen effect. This improves the dynamic response frequency of the probe and avoids the tedious work and measurement uncertainty caused by probe transfer function calibration. 3. This scheme uses a single differential pressure sensor to directly measure the pressure difference between the left and right holes and the top and bottom holes. Compared with the traditional five-hole probe method of using two pressure sensors to measure the pressure of the left and right or top and bottom holes separately and then calculating the difference, it reduces the measurement uncertainty. 4. Based on the probe head configuration, this scheme constructs new probe calibration coefficients and calculates aerodynamic parameters such as total pressure and static pressure, thereby improving measurement accuracy.

[0060] The above are merely several specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

[0061] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0062] It should be noted that, in the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

Claims

1. A miniature dynamic porous probe, characterized in that, Includes a probe, which is placed in the flow field being measured. The probe includes a pressure measuring part, which is provided with a first pressure measuring hole (1), a second pressure measuring hole (2), a third pressure measuring hole (3), a fourth pressure measuring hole (4) and a fifth pressure measuring hole (5), and the probe is provided with a sixth pressure measuring hole (6). The first pressure measuring hole (1) and the third pressure measuring hole (3) extend to both sides of the first differential pressure sensor (7), the fourth pressure measuring hole (4) and the fifth pressure measuring hole (5) extend to both sides of the second differential pressure sensor (8), the second pressure measuring hole (2) extends to the first pulsating pressure sensor (9), and the sixth pressure measuring hole (6) extends to the second pulsating pressure sensor (10).

2. The micro dynamic porous probe according to claim 1, characterized in that, The pressure measuring part is hemispherical, and the second pressure measuring hole (2) is located at the top of the hemispherical surface of the pressure measuring part along the axial direction. The first pressure measuring hole (1), the third pressure measuring hole (3), the fourth pressure measuring hole (4) and the fifth pressure measuring hole (5) are located on the hemispherical surface of the pressure measuring part and are evenly distributed circumferentially with the second pressure measuring hole (2) as the center.

3. The micro dynamic porous probe according to claim 2, characterized in that, The angle between the first pressure measuring hole (1) and the axis of the probe is 30°~35°, the angle between the fourth pressure measuring hole (4) and the axis of the probe is 40°~45°, and the extension length of the second pressure measuring hole (2) is 1~2mm.

4. The micro dynamic porous probe according to claim 1, characterized in that, The sixth pressure measuring hole (6) is located on the side of the probe and outside the pressure measuring part. The sixth pressure measuring hole (6) extends radially inward along the probe and the extension length is 1~2mm.

5. The micro dynamic porous probe according to claim 1, characterized in that, The diameters of the first pressure measuring hole (1), the second pressure measuring hole (2), the third pressure measuring hole (3), the fourth pressure measuring hole (4), the fifth pressure measuring hole (5), and the sixth pressure measuring hole (6) are all 0.4~0.6mm.

6. The micro dynamic porous probe according to claim 1, characterized in that, The miniature dynamic porous probe also includes a support rod connected to the end of the probe away from the pressure measuring part.

7. A calibration method for a miniature dynamic porous probe, characterized in that, Using the micro dynamic porous probe as described in any one of claims 1 to 6, the method comprises the following steps: The micro dynamic porous probe was used to measure the physical parameters under different working conditions in a wind tunnel, and the calibration fitting relationship between the aerodynamic coefficient and the measured physical parameters was obtained through data fitting.

8. The calibration method according to claim 7, characterized in that, The measured physical parameters include Mach number, yaw angle, and pitch angle, and the aerodynamic coefficients include yaw angle coefficient, pitch angle coefficient, total pressure coefficient, and static pressure coefficient.

9. The calibration method according to claim 8, characterized in that, The micro dynamic porous probe is used for calibration in a wind tunnel. The Mach number, yaw angle, and pitch angle are controlled to vary within the operating range to obtain the calibration fitting relationship between the aerodynamic coefficient and the measured physical parameter within the calibration range. The calibration range includes a Mach number of 0.2 to 0.8, a yaw angle of -30° to +30°, and a pitch angle of -20° to +20°.

10. The calibration method according to claim 9, characterized in that, The obtained calibration fitting relationships include the first fitting relationship, the second fitting relationship, the third fitting relationship, and the fourth fitting relationship, which are as follows: in, This is the yaw angle coefficient; This is the pitch angle coefficient; This is the total pressure coefficient; This is the static pressure coefficient; The pressure gauge at the center hole; The pressure difference between the left and right orifices; The pressure difference between the upper and lower holes; Quasi-static pressure; Total pressure; It is static pressure; It is the Mach number; Yaw angle; It is the pitch angle.

11. A method of using a miniature dynamic porous probe, characterized in that, Using the micro dynamic porous probe as described in any one of claims 1 to 6, the method comprises the following steps: The pressure difference between the left and right holes, the pressure difference between the upper and lower holes, the gauge pressure of the center hole, and the quasi-static pressure were measured using the aforementioned micro dynamic multi-hole probe. Based on the pressure difference between the left and right holes, the pressure difference between the upper and lower holes, the gauge pressure of the center hole, and the quasi-static pressure, the yaw angle coefficient and the pitch angle coefficient are obtained. Based on the selected first Mach number, a first fitting relationship is obtained between the yaw angle coefficient and the yaw angle and pitch angle. Based on the selected first Mach number, a second fitting relationship is obtained between the pitch angle coefficient and the yaw angle and pitch angle. The yaw angle and pitch angle are obtained based on the first and second fitting relationships; The total pressure coefficient and static pressure coefficient are obtained based on the third and fourth fitting relationships; The total pressure and static pressure are obtained based on the total pressure coefficient and static pressure coefficient; The second Mach number is obtained based on total pressure and static pressure; If the residual between the first Mach number and the second Mach number is greater than or equal to the residual threshold, then the first fitting relationship and the second fitting coefficient are obtained based on the second Mach number, and the relevant parameters are recalculated until the residual is less than the residual threshold.

12. The method of use according to claim 11, characterized in that, The first fitting relationship, the second fitting relationship, the third fitting relationship, and the fourth fitting relationship are as follows: in, This is the yaw angle coefficient; This is the pitch angle coefficient; This is the total pressure coefficient; This is the static pressure coefficient; The pressure gauge at the center hole; The pressure difference between the left and right orifices; The pressure difference between the upper and lower holes; Quasi-static pressure; Total pressure; It is static pressure; It is the Mach number; Yaw angle; It is the pitch angle.

13. The method of use according to claim 11, characterized in that, The process of obtaining the second Mach number based on total pressure and static pressure includes solving for the second Mach number based on the total pressure and static pressure according to the isentropic process parameter relationship, wherein the isentropic process parameter relationship is as follows: in, It is the second Mach number; Total pressure; It is static pressure; It represents the adiabatic index.

14. The method of use according to claim 11, characterized in that, The residual threshold is 0.01.

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