High-dynamic pneumatic probe calibration method and calibration device thereof

Abstract

The invention belongs to the field of test fluid mechanics, and discloses a high-dynamic pneumatic probe calibration method and a calibration device thereof. The high-dynamic pneumatic probe calibration device comprises a probe supporting assembly and a two-degree-of-freedom supporting assembly, wherein the probe supporting assembly is fixed at the front end of the two-degree-of-freedom supporting assembly through a connecting plate; a servo motor is installed in the probe supporting assembly, the servo motor swings the probe at a high frequency under the stable incoming flow condition to simulate the high-dynamic flow field condition, and decoupling of the speed and the angle in the dynamic calibration process of the probe is achieved. According to the high-dynamic pneumatic probe calibration method, real-time pressure data of all pressure sensing holes of a probe serve as input, the real-time Mach number, the incidence angle and the sideslip angle of a flow field serve as output, a neural network method is adopted for modeling and data analysis, a calibration curve of probe dynamic flow field measurement is obtained, and calibration of the dynamic pneumatic probe is completed. According to the high-dynamic pneumatic probe calibration method and the calibration device thereof, the measurement precision of the pneumatic probe in a high-dynamic flow field is improved, and the high-dynamic pneumatic probe calibration method and the calibration device have engineering practical value.

Description

Technical Field

[0001] This invention belongs to the field of experimental fluid mechanics, and specifically relates to a high-dynamic pneumatic probe calibration method and calibration device. Background Technology

[0002] A pneumatic probe is a device for measuring the physical parameters (direction, velocity, etc.) of airflow. It boasts advantages such as simple structure, ease of use, and high measurement accuracy, making it the most traditional and reliable method for flow field testing. It is widely used in aerospace, fluid machinery, and many other fields. The head of the pneumatic probe has several pressure holes; the direction and velocity of the airflow are calculated by observing the pressure changes in each hole. Commonly used pneumatic probes come in various forms, including single-hole, three-hole, five-hole, and seven-hole probes.

[0003] The calibration method for pneumatic probes often employs experimental calibration, which involves conducting a blowing test in a wind tunnel. The probe to be calibrated is installed in a high-quality calibration wind tunnel, which generates a precisely known, uniform, and stable free flow. By changing the velocity of the incoming flow, the probe's angle of attack, and yaw angle through the wind tunnel's measurement and control system, the pressure readings of each pressure sensor on the probe are recorded under different operating conditions. Then, by establishing a model formula for the dimensionless parameters between Mach number, angle of attack, sideslip angle, and the measured values ​​of different pressure sensors, the flow field parameters can be inversely calculated from pressure. The accuracy of traditional calibration methods is significantly affected by flow field fluctuations and is only suitable for calibration in steady flow fields where the incoming flow parameters remain stable in both time and space. For highly dynamic or non-uniform flow fields, traditional calibration methods struggle to capture the instantaneous changes in the flow field, and the reliability of the calibration results decreases significantly.

[0004] In highly dynamic flow fields, the flow velocity, direction angle, and other parameters exhibit dramatic, rapid, and large fluctuations in both space and time. Consequently, the pressure monitoring data from aerodynamic probes also exhibits unsteady, high-frequency fluctuations. Traditional calibration methods, based on steady-state flow field parameters, produce numerous distortions and are no longer applicable. Therefore, to meet the calibration requirements of aerodynamic probes in highly dynamic flow fields, it is necessary to develop a highly dynamic aerodynamic probe calibration method and its calibration device. This method should be able to simulate the dynamic changes in the incoming flow direction through probe dynamic oscillation, based on the steady-state flow field generated by the calibration wind tunnel, thereby simulating the highly dynamic flow field and completing the calibration of the highly dynamic aerodynamic probe. Summary of the Invention

[0005] One technical problem to be solved by the present invention is to provide a high dynamic pneumatic probe calibration device, and another technical problem to be solved by the present invention is to provide a high dynamic pneumatic probe calibration method, so as to overcome the defects of the prior art.

[0006] The high dynamic pneumatic probe calibration device of the present invention includes a probe support assembly and a two-degree-of-freedom support assembly for fixing the probe support assembly; The probe support assembly comprises a bracket, an encoder assembly, a probe tool, a servo motor, a probe, a counterweight and a connecting plate I; the bracket is a frame; the left frame of the bracket fixes the probe tool, the servo motor is fixed on the probe tool, a probe perpendicular to the flow direction is fixed on the output shaft of the servo motor, the front end of the probe is bent by 90 DEG to face the flow, and the encoder assembly is arranged on the servo motor; the right frame of the bracket fixes the counterweight matched with the servo motor; and the lower frame of the bracket fixes the connecting plate I; The two-degree-of-freedom support assembly comprises a connecting plate II, an angle-of-attack alpha arc-shaped rack, a sideslip angle beta arc-shaped rack, a large connecting plate and a probe holder; the two-degree-of-freedom support assembly is fixed in the test cabin through the large connecting plate at the bottom; the front end of the large connecting plate fixes the sideslip angle beta arc-shaped rack; the top surface of the large connecting plate fixes the angle-of-attack alpha arc-shaped rack, the top end of the angle-of-attack alpha arc-shaped rack fixes the probe holder, and the top surface of the large connecting plate also fixes the connecting plate II; The lower frame of the bracket of the probe support assembly is fixed on the connecting plate II of the two-degree-of-freedom support assembly through the connecting plate I; For the combined use case that the probe is fixed on the output shaft of the servo motor: the sideslip angle beta of the probe is adjusted and controlled through the sideslip angle beta arc-shaped rack, and the sideslip angle beta is continuously adjustable within ±60 DEG ; the angle-of-attack alpha of the probe is adjusted and controlled through the encoder assembly, and the angle-of-attack alpha is continuously adjustable within ±60 DEG ; For the separate use case that the probe is fixed on the probe holder: the sideslip angle beta of the probe is adjusted and controlled through the sideslip angle beta arc-shaped rack, and the sideslip angle beta is continuously adjustable within ±60 DEG ; the angle-of-attack alpha of the probe is adjusted and controlled through the angle-of-attack alpha arc-shaped rack, and the adjustment range of the angle-of-attack alpha depends on the adjustment range of the angle-of-attack alpha arc-shaped rack.

[0007] The high-dynamic aerodynamic probe calibration method comprises the following steps: S10. Determining the test task of the dynamic aerodynamic probe calibration device; The dynamic aerodynamic probe calibration device is suitable for carrying out wind tunnel tests; after the dynamic aerodynamic probe calibration device is completed, the dynamic aerodynamic probe calibration device can be used separately or in combination: when used in combination, the probe is installed on the probe tool to carry out probe calibration work; when used separately, the probe is installed on the probe holder of the two-degree-of-freedom support assembly to carry out probe calibration work; the test task of the dynamic aerodynamic probe calibration device is determined according to requirements; S20. Determining a dynamic flow field simulation scheme; The dynamic flow field simulation is performed in combination, and the dynamic flow field simulation is achieved by the steady flow field generated by the calibration wind tunnel and the swing of the probe; wherein the swing of the probe is achieved by a servo motor; the inlet of the probe is coaxial with the center line of the nozzle and faces the incoming flow, and during the swing of the probe by the servo motor, the position of the inlet of the probe remains stable, and the angle of the incoming flow does not change with the swing of the probe, thereby achieving decoupled adjustment of the incoming flow velocity and angle; the swing frequency of the probe is continuously adjustable within the range of 0-10 Hz, the angle of attack of the probe is continuously adjustable within ±60°, and the sideslip angle of the probe is continuously adjustable within ±60°; S30. Perform dynamic flow field information measurement scheme evaluation; In the calibration wind tunnel, a commercial standard five-hole probe is used to test the dynamic flow field; under different Mach numbers, angles of attack, sideslip angles, and amplitudes, the influence of the technical parameters such as the length of the pressure measurement pipeline and the sampling rate of the pressure scanning valve in the dynamic calibration process is evaluated, the variation law of the pressure measurement value of the pressure sensing hole and the sensitivity of the pressure measurement value of the pressure sensing hole to the flow change are analyzed, and the technical parameters such as the length of the pressure measurement pipeline and the sampling rate of the pressure scanning valve in the dynamic calibration process are determined; S40. Perform probe dynamic calibration test; According to the dynamic flow field simulation scheme of S20, the probe is installed in the probe tooling, and then the dynamic aerodynamic probe calibration device is installed in the test chamber of the calibration wind tunnel, the inlet of the probe is adjusted to be coaxial with the center line of the nozzle and faces the incoming flow; the technical parameters determined in S30 are used to change the angle of attack and the sideslip angle through the two-degree-of-freedom support assembly, and single-degree-of-freedom oscillation is performed, so that the probe is calibrated in the dynamic flow field, and calibration test data is obtained; S50. Analyze the calibration test data and complete the nonlinear calibration analysis modeling; The real-time pressure data of the different pressure sensing holes of the probe obtained in S40 are used as the training input of the BP neural network, the real-time Mach number, angle of attack, and sideslip angle of the dynamic flow field are used as the training output of the BP neural network, the dynamic aerodynamic probe calibration model is trained by using the BP neural network, the calibration curve of the probe dynamic flow field measurement is obtained, the aerodynamic probe calculation model for the high dynamic flow field is established, and the probe calibration file is formed; the BP neural network includes inputs, 3 outputs, a hidden layer including neurons, the hidden layer uses a Tan-sigmoid transfer function, the neurons of the output layer use a Linear transfer function, the activation function uses a ReLu function, and the overall neural network structure is , and the iteration training is performed times, and the loss function is selected as MSE, which is defined as: ; wherein, denotes a real value, is a corresponding predicted value, is a sample number; The input-output relationship of a neuron model is represented as: ; wherein, is an input signal from other cells, is a bias of the neuron, denotes the connection weight of the cell to the cell , is the number of input signals, is the input, is a transfer function; S60. Perform probe dynamic measurement precision verification; Adjust the Mach number, angle of attack α, side slip angle β of the dynamic flow field, repeatedly measure multiple times using the same probe, input the obtained measurement data into the probe calibration file, compare and analyze the output results, and obtain the measurement precision of the probe under dynamic conditions.

[0008] Further, the specific steps of S40 are as follows: S41. Adjust the incoming flow velocity to a fixed Mach number and maintain stability, adjust the angle of attack α and side slip angle β of the probe one by one through the servo motor and two-degree-of-freedom support assembly to find the aerodynamic zero point of the probe; record the specific value of the displacement mechanism when the probe is located at the aerodynamic zero point, and then set the displacement mechanism to the mechanical zero position; S42. Stably maintain the incoming flow velocity at a predetermined Mach number, start the servo motor to perform dynamic oscillation of the probe to simulate a dynamic flow field; fix the angle of attack α, adjust the side slip angle β to the preset value according to the test schedule, ensure that the inlet of the probe is coaxial with the center line of the nozzle and faces the incoming flow during the adjustment process, and after the pressure data measured by the probe reaches stability, start data acquisition and record the total temperature, total pressure, static pressure in the wind tunnel, atmospheric pressure and pressure at the output port of the probe in detail; S43. After completing the data acquisition of the current side slip angle β, repeat the above steps to perform data acquisition on the remaining side slip angles β under the same angle of attack α, and when all side slip angles β under an angle of attack α have completed data acquisition, change the angle of attack α of the probe and continue to perform data acquisition on all side slip angles β under this angle of attack α, repeat the above work until data acquisition on all side slip angles β under all angles of attack α is completed, and all calibration test data are obtained.

[0009] The high-dynamic aerodynamic probe calibration method and the calibration device thereof have the following characteristics: 1. The dynamic change of the flow direction is simulated by the dynamic oscillation of the probe, the highest simulation frequency can reach 10 Hz, which ensures the real-time change of the flow size and angle, provides a known, accurate and high dynamic non-steady flow simulation, the dynamic oscillation of the probe is realized by a servo motor, the weight of the servo motor will affect the stability of the probe support assembly, therefore, a counterweight is added on the other side of the servo motor, which is used for balancing the whole probe support assembly and reducing the test error caused by the vibration of the probe support assembly during the working process; 2. The change rule of the pressure measurement value of the pressure sensing hole and the sensitivity to the flow change under different Mach numbers, angles of attack α, sideslip angles β and amplitudes are analyzed by using a commercial standard five-hole probe for dynamic flow field development test, and the technical parameters such as the length of the pressure measurement pipeline and the sampling rate of the pressure scanning valve during the test process are dynamically evaluated; 3. During the dynamic calibration test of the probe, the sideslip angle β is changed by the sideslip angle β arc rack of the two-degree-of-freedom support assembly, the angle of attack α is adjusted by the swing of the servo motor, and the dynamic oscillation of the probe is realized by the swing of the servo motor.

[0010] The high dynamic aerodynamic probe calibration device of the application comprises a probe support assembly and a two-degree-of-freedom support assembly, the probe support assembly is fixed at the front end of the two-degree-of-freedom support assembly through a connecting plate; a servo motor is installed in the probe support assembly, the high dynamic flow field condition is simulated by the high-frequency swing of the servo motor under the condition of stable flow, and the decoupling of the speed and angle during the dynamic calibration of the probe is realized; the high dynamic aerodynamic probe calibration method of the application takes the real-time pressure data of each pressure sensing hole of the probe as the input, takes the real-time Mach number, angle of attack and sideslip angle of the flow field as the output, adopts the neural network method to model and analyze the data, obtains the calibration curve of the dynamic flow field measurement of the probe, and completes the calibration of the dynamic aerodynamic probe.

[0011] The high dynamic aerodynamic probe calibration method and the calibration device thereof of the application simulate the running condition of the aerodynamic probe in the high dynamic flow field environment, realize the calibration of the aerodynamic probe in the high dynamic flow field, and improve the measurement precision of the aerodynamic probe in the high dynamic flow field. The swing frequency of the servo motor is continuously adjustable in the range of 0-10 Hz, the angle of attack is continuously adjustable in the range of ±60°, and the sideslip angle is continuously adjustable in the range of ±60°. It has strong engineering practical value. BRIEF DESCRIPTION OF DRAWINGS

[0012] Figure 1 It is a structural schematic view of the high dynamic aerodynamic probe calibration device of the application; Figure 2 It is a structural schematic view of the probe support assembly in the high dynamic aerodynamic probe calibration device of the application; Figure 3 It is a structural schematic view of the servo motor in the high dynamic aerodynamic probe calibration device of the application; Figure 4 This is a schematic diagram of the two-degree-of-freedom support assembly in the high-dynamic pneumatic probe calibration device of the present invention. Figure 5 A schematic diagram showing the adjustment of the sideslip angle β of a two-degree-of-freedom support assembly; Figure 6 A schematic diagram showing the adjustment of the angle of attack α of the two-degree-of-freedom support assembly when used alone; Figure 7 This is a flowchart of the high-dynamic pneumatic probe calibration method of the present invention.

[0013] In the figure, 1. Probe support assembly; 2. Two-degree-of-freedom support assembly; 1-1. Bracket; 1-2. Encoder assembly; 1-3. Probe fixture; 1-4. Servo motor; 1-5. Probe; 1-6. Counterweight; 1-7. Connecting plate I; 2-1. Connecting plate II; 2-2. Angle of attack α arc rack; 2-3. Side slip angle β arc rack; 2-4. Large connecting plate; 2-5. Probe holder. Detailed Implementation

[0014] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0015] Example: Figures 1-4 As shown, the high dynamic pneumatic probe calibration device of this embodiment includes a probe support assembly 1 and a two-degree-of-freedom support assembly 2 that fixes the probe support assembly 1. The probe support assembly 1 includes a bracket 1-1, an encoder assembly 1-2, a probe fixture 1-3, a servo motor 1-4, a probe 1-5, a counterweight 1-6, and a connecting plate I 1-7. The bracket 1-1 is a frame. The probe fixture 1-3 is fixed to the left frame of the bracket 1-1, and the servo motor 1-4 is fixed to the probe fixture 1-3. The probe 1-5, which is perpendicular to the incoming flow direction, is fixed to the output shaft of the servo motor 1-4. The front end of the probe 1-5 is bent at 90° to face the incoming flow. The encoder assembly 1-2 is installed on the servo motor 1-4. The counterweight 1-6, which matches the servo motor 1-4, is fixed to the right frame of the bracket 1-1. The connecting plate I 1-7 is fixed to the lower frame of the bracket 1-1. The two-degree-of-freedom support assembly 2 includes a connecting plate II 2-1, an arc-shaped rack with an angle of attack α 2-2, an arc-shaped rack with a side-slip angle β 2-3, a large connecting plate 2-4, and a probe holder 2-5. The two-degree-of-freedom support assembly 2 is fixed in the test chamber by the large connecting plate 2-4 at the bottom. The arc-shaped rack with a side-slip angle β 2-3 is fixed to the front end of the large connecting plate 2-4. The arc-shaped rack with an angle of attack α 2-2 is fixed to the top surface of the large connecting plate 2-4, and the probe holder 2-5 is fixed to the top end of the arc-shaped rack with an angle of attack α 2-2. The connecting plate II 2-1 is also fixed to the top surface of the large connecting plate 2-4. The lower frame of the bracket 1-1 of the probe support assembly 1 is fixed on the connecting plate II 2-1 of the two-degree-of-freedom support assembly 2 through the connecting plate I 1-7; For the combined use case that the probe 1-5 is fixed on the output shaft of the servo motor 1-4: as shown in Figure 5 The side slip angle β of the probe 1-5 is adjusted and controlled through the side slip angle β arc-shaped rack 2-3, and the side slip angle β is continuously adjustable within ±60°; as shown in Figure 3 The angle of attack α of the probe 1-5 is adjusted and controlled through the encoder assembly 1-2, and the angle of attack α is continuously adjustable within ±60°; For the separate use case that the probe 1-5 is fixed on the probe holder 2-5: as shown in Figure 5 The side slip angle β of the probe 1-5 is adjusted and controlled through the side slip angle β arc-shaped rack 2-3, and the side slip angle β is continuously adjustable within ±60°; as shown in Figure 6 The angle of attack α of the probe 1-5 is adjusted and controlled through the angle of attack α arc-shaped rack 2-2, and the adjustment range of the angle of attack α depends on the adjustment range of the angle of attack α arc-shaped rack 2-2.

[0016] As shown in Figure 7 The high-dynamic pneumatic probe calibration method of the embodiment comprises the following steps: S10. Determine the test task of the dynamic pneumatic probe calibration device; The dynamic pneumatic probe calibration device is suitable for carrying out wind tunnel tests; after the dynamic pneumatic probe calibration device is completed, it can be used separately or in combination: when used in combination, the probe 1-5 is installed on the probe tool 1-3 to carry out probe calibration work; when used separately, the probe 1-5 is installed on the probe holder 2-5 of the two-degree-of-freedom support assembly 2 to carry out probe calibration work; determine the test task of the dynamic pneumatic probe calibration device according to requirements; S20. Determine the dynamic flow field simulation scheme; When used in combination, the dynamic flow field simulation is achieved by the steady flow field generated by the calibration wind tunnel and the swing of the probe 1-5; wherein the swing of the probe 1-5 is realized by the servo motor 1-4; the inlet of the probe 1-5 is coaxial with the center line of the nozzle and faces the incoming flow; during the process of swinging the probe 1-5 by the servo motor 1-4, the position of the inlet of the probe 1-5 remains stable, and the angle of the incoming flow does not change with the swing of the probe 1-5, realizing the decoupling adjustment of the incoming flow velocity and angle; the swing frequency of the probe 1-5 is continuously adjustable within the range of 0~10Hz, the angle of attack α of the probe 1-5 is continuously adjustable within ±60°, and the side slip angle β of the probe 1-5 is continuously adjustable within ±60°; S30. Evaluate the dynamic flow field information measurement scheme; In the calibration wind tunnel, the commercial standard five-hole probe is used to test the dynamic flow field; under different Mach numbers, angles of attack alpha, sideslip angles beta, amplitudes, the influence of the technical parameters such as the length of the pressure measuring pipe, the sampling rate of the pressure scanning valve in the dynamic calibration process is evaluated, the variation law of the pressure measurement value of the pressure sensing hole and the sensitivity of the pressure measurement value of the pressure sensing hole to the flow change are analyzed, and the technical parameters such as the length of the pressure measuring pipe, the sampling rate of the pressure scanning valve in the dynamic calibration process are determined; S40. Develop probe dynamic calibration test; According to the dynamic flow field simulation scheme of S20, the probes 1-5 are installed in the probe tooling 1-3, and then the dynamic aerodynamic probe calibration device is installed in the test chamber of the calibration wind tunnel, the inlet of the probe 1-5 is adjusted to be coaxial with the center line of the nozzle and facing the incoming flow; the technical parameters determined in S30 are used to change the angle of attack alpha and the sideslip angle beta through the two-degree-of-freedom support assembly 2, and single-degree-of-freedom oscillation is performed, so that the probe 1-5 is in a dynamic flow field for calibration, and calibration test data is obtained; S50. Analyze calibration test data and complete nonlinear calibration analysis modeling; The real-time pressure data of different pressure sensing holes of the probe 1-5 obtained in S40 are used as the training input of the BP neural network, and the real-time Mach number, angle of attack alpha and sideslip angle beta of the dynamic flow field are used as the training output of the BP neural network, the dynamic aerodynamic probe calibration model is trained by using the BP neural network, the calibration curve of the probe dynamic flow field measurement is obtained, the aerodynamic probe calculation model for high dynamic flow field is established, and the probe calibration file is formed; the BP neural network includes inputs, 3 outputs, a hidden layer including neurons, the hidden layer uses a Tan-sigmoid transfer function, the neurons of the output layer use a Linear transfer function, the activation function uses a ReLu function, and the overall neural network structure is , a total of iterations, and the loss function is selected as MSE, which is defined as: ; Wherein, represents the true value, is the corresponding predicted value, is the number of samples; The input-output relationship of a neuron model is represented as: ; Wherein, is the input signal from other cells, is the bias of the neuron, represents the connection weight of the cell to the cell , the number of input signals, the input, the transfer function; S60. Perform probe dynamic measurement accuracy check; Adjust the Mach number, angle of attack α, side slip angle β of the dynamic flow field, repeat the measurement for multiple times using the same probe 1-5, input the obtained measurement data into the probe calibration file, compare and analyze the output results, and obtain the measurement accuracy of the probe 1-5 under dynamic conditions.

[0017] Further, the specific steps of S40 are as follows: S41. Adjust the incoming flow velocity to a fixed Mach number and maintain stability, adjust the angle of attack α and side slip angle β of the probe 1-5 one by one through the servo motor 1-4 and the two-degree-of-freedom support assembly 2 to find the aerodynamic zero point of the probe 1-5; record the specific value of the displacement mechanism of the probe 1-5 at the aerodynamic zero point, and then set the displacement mechanism to the mechanical zero point; S42. Stably maintain the incoming flow velocity at a predetermined Mach number, start the servo motor 1-4 to perform dynamic oscillation of the probe 1-5 to simulate a dynamic flow field; fix the angle of attack α, adjust the side slip angle β to the preset value according to the test schedule, ensure the inlet of the probe 1-5 coaxial with the center line of the nozzle and facing the incoming flow during the adjustment process, and after the pressure data measured by the probe 1-5 reaches stability, start data acquisition and record the total temperature, total pressure, static pressure in the wind tunnel, atmospheric pressure and pressure at the output port of the probe in detail; S43. After completing the data acquisition of the current side slip angle β, repeat the above steps to perform data acquisition of the remaining side slip angles β one by one under the same angle of attack α, change the angle of attack α of the probe 1-5 after the data acquisition of all side slip angles β under one angle of attack α is completed, and continue to perform data acquisition of all side slip angles β under the angle of attack α, repeat the above work until the data acquisition of all side slip angles β under all angles of attack α is completed, and obtain all calibration test data.

[0018] Although the embodiments of the present application have been disclosed as above, they are not limited to the application listed in the specification and the embodiments, and all features disclosed in the present application, or steps in all methods or processes disclosed in the present application, except for mutually exclusive features and / or steps, can be combined in any manner, and the present application is not limited to specific details and the figures shown and described herein.

Claims

1. A high dynamic aerodynamic probe calibration device, characterized by, The dynamic aerodynamic probe calibration device comprises a probe support assembly (1) and a two-degree-of-freedom support assembly (2) for fixing the probe support assembly (1); The probe support assembly (1) comprises a bracket (1-1), an encoder assembly (1-2), a probe tooling (1-3), a servo motor (1-4), a probe (1-5), a counterweight (1-6) and a connecting plate I (1-7); the bracket (1-1) is a frame; the left frame of the bracket (1-1) is fixed with the probe tooling (1-3), the servo motor (1-4) is fixed on the probe tooling (1-3), a probe (1-5) perpendicular to the flow direction is fixed on the output shaft of the servo motor (1-4), the front end of the probe (1-5) is bent by 90° to face the flow, and the servo motor (1-4) is provided with the encoder assembly (1-2); the right frame of the bracket (1-1) is fixed with the counterweight (1-6) matched with the servo motor (1-4); and the lower frame of the bracket (1-1) is fixed with the connecting plate I (1-7); The two-degree-of-freedom support assembly (2) comprises a connecting plate II (2-1), an angle-of-attack alpha arc-shaped rack (2-2), a sideslip angle beta arc-shaped rack (2-3), a large connecting plate (2-4) and a probe holder (2-5); the two-degree-of-freedom support assembly (2) is fixed in the test cabin through the large connecting plate (2-4) at the bottom; the front end of the large connecting plate (2-4) is fixed with the sideslip angle beta arc-shaped rack (2-3); the top surface of the large connecting plate (2-4) is fixed with the angle-of-attack alpha arc-shaped rack (2-2), the top end of the angle-of-attack alpha arc-shaped rack (2-2) is fixed with the probe holder (2-5), and the top surface of the large connecting plate (2-4) is further fixed with the connecting plate II (2-1); The lower frame of the bracket (1-1) of the probe support assembly (1) is fixed on the connecting plate II (2-1) of the two-degree-of-freedom support assembly (2) through the connecting plate I (1-7); For the combined use case that the probe (1-5) is fixed on the output shaft of the servo motor (1-4): the sideslip angle beta of the probe (1-5) is adjusted and controlled through the sideslip angle beta arc-shaped rack (2-3), and the sideslip angle beta is continuously adjustable within ±60°; the angle-of-attack alpha of the probe (1-5) is adjusted and controlled through the encoder assembly (1-2), and the angle-of-attack alpha is continuously adjustable within ±60°; For the separate use case that the probe (1-5) is fixed on the probe holder (2-5): the sideslip angle beta of the probe (1-5) is adjusted and controlled through the sideslip angle beta arc-shaped rack (2-3), and the sideslip angle beta is continuously adjustable within ±60°; the angle-of-attack alpha of the probe (1-5) is adjusted and controlled through the angle-of-attack alpha arc-shaped rack (2-2), and the adjustment range of the angle-of-attack alpha depends on the adjustment range of the angle-of-attack alpha arc-shaped rack (2-2).

2. A method of calibrating a high dynamic range aerodynamic probe for use in the high dynamic range aerodynamic probe calibration apparatus of claim 1, the method comprising: The method comprises the following steps: S10. determining the test task of the dynamic aerodynamic probe calibration device; The dynamic aerodynamic probe calibration device is suitable for carrying out wind tunnel test; the dynamic aerodynamic probe calibration device can be used alone or in combination after being completed; when used in combination, the probes (1-5) are installed on the probe tooling (1-3) to carry out probe calibration; when used alone, the probes (1-5) are installed on the probe clamps (2-5) of the two-degree-of-freedom support assembly (2) to carry out probe calibration; the test task of the dynamic aerodynamic probe calibration device is determined according to requirements; S20. Determine the dynamic flow field simulation scheme; When used in combination, the dynamic flow field simulation is carried out by generating a steady flow field in the calibration wind tunnel and swinging the probe (1-5); wherein the swinging of the probe (1-5) is realized by the servo motor (1-4); the inlet of the probe (1-5) is coaxial with the center line of the nozzle and faces the incoming flow; during the process of swinging the probe (1-5) by the servo motor (1-4), the position of the inlet of the probe (1-5) remains stable, and the angle of the incoming flow does not change with the swinging of the probe (1-5), realizing the decoupling adjustment of the incoming flow velocity and angle; the swinging frequency of the probe (1-5) is continuously adjustable in the range of 0~10Hz, the angle of attack α of the probe (1-5) is continuously adjustable in the range of ±60°, and the sideslip angle β of the probe (1-5) is continuously adjustable in the range of ±60°; S30. Evaluate the dynamic flow field information measurement scheme; In the calibration wind tunnel, a commercial standard five-hole probe is used to test the dynamic flow field; under different Mach numbers, angles of attack α, sideslip angles β and amplitudes, the influence of technical parameters such as the length of the pressure measurement pipeline and the sampling rate of the pressure scanning valve in the dynamic calibration process is evaluated, the variation law of the pressure measurement value of the pressure sensing hole and the sensitivity of the pressure measurement value of the pressure sensing hole to the flow change are analyzed, and the technical parameters such as the length of the pressure measurement pipeline and the sampling rate of the pressure scanning valve in the dynamic calibration process are determined; S40. Carry out probe dynamic calibration test; According to the dynamic flow field simulation scheme of S20, the probe (1-5) is installed in the probe tooling (1-3), and then the dynamic aerodynamic probe calibration device is installed in the test cabin of the calibration wind tunnel; the inlet of the probe (1-5) is adjusted to be coaxial with the center line of the nozzle and face the incoming flow; the technical parameters determined in S30 are used to change the angle of attack α and the sideslip angle β through the two-degree-of-freedom support assembly (2) and carry out single-degree-of-freedom oscillation, so that the probe (1-5) is calibrated in the dynamic flow field to obtain calibration test data; S50. Analyze the calibration test data and complete the non-linear calibration analysis modeling; The different pressure hole real-time pressure data of the probe (1-5) obtained by S40 is taken as the training input of the BP neural network, the dynamic flow field real-time Mach number, the angle of attack alpha and the side slip angle beta are taken as the training output of the BP neural network, the dynamic aerodynamic probe calibration model is trained by using the BP neural network, the calibration curve of the probe dynamic flow field measurement is obtained, the aerodynamic probe calculation model for the high dynamic flow field is established, and the probe calibration file is formed; the BP neural network comprises an input, 3 outputs, a hidden layer comprising a neuron, the hidden layer adopts a Tan-sigmoid transfer function, the neuron of the output layer adopts a Linear transfer function, the activation function adopts a ReLu function, the overall neural network structure is , the iteration training is performed for a total of times, and the loss function is selected as MSE, which is defined as: ； wherein, represents a true value, is a corresponding predicted value, is the number of samples; The input-output relationship of a neuron model is represented as: ； wherein, is an input signal from other cells, is a bias of the neuron, represents a cell to which the neuron is connected, is a connection weight from the cell is the number of input signals, is the input, is a transfer function; S60. Probe dynamic measurement precision checking; The Mach number, angle of attack α and sideslip angle β of the dynamic flow field are adjusted, the same probe (1-5) is repeatedly measured for multiple times, the obtained measurement data is input into the probe calibration file, the output results are compared and analyzed, and the measurement precision of the probe (1-5) under dynamic conditions is obtained.

3. The high dynamic range aerodynamic probe calibration method of claim 2, wherein, The specific steps of S40 are as follows: S41. Adjust the incoming flow velocity to a fixed Mach number and maintain stability, adjust the angle of attack α and the side slip angle β of the probe (1-5) one by one through the servo motor (1-4) and the two-degree-of-freedom support assembly (2) to find the aerodynamic zero point of the probe (1-5); Record the specific value of the displacement mechanism when the probe (1-5) is at the aerodynamic zero point, and then set the displacement mechanism to the mechanical zero point; S42. Keep the incoming flow velocity stable at the predetermined Mach number, open the servo motor (1-4) to perform dynamic oscillation of the probe (1-5) to simulate the dynamic flow field; Fix the angle of attack α, adjust the side slip angle β to the preset value according to the test schedule, ensure the inlet of the probe (1-5) coaxial with the nozzle centerline and facing the incoming flow during the adjustment process, and after the pressure data measured by the probe (1-5) reaches stability, start data collection and record the total temperature, total pressure, static pressure in the wind tunnel, atmospheric pressure and pressure at the output port of the probe in detail; S43. After completing the data collection of the current side slip angle β, repeat the above steps to collect data for the remaining side slip angles β under the same angle of attack α, and when all side slip angles β under an angle of attack α have completed data collection, change the angle of attack α of the probe (1-5) and continue to collect data for all side slip angles β under this angle of attack α. Repeat the above work until all side slip angles β under all angles of attack α have completed data collection and all calibration test data are obtained.

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