Wind tunnel continuous force measurement test method

Abstract

The invention discloses a wind tunnel continuous force measurement test method, and belongs to the technical field of wind tunnel force measurement tests. In order to solve the problem that the precision of a wind tunnel continuous force measurement test is not high when the Mach number is large, the method comprises the steps that a wind tunnel test supporting system, a force measurement test balance and a test model are installed in a wind tunnel, and a windless test is carried out to obtain windless test data; performing a wind test, and collecting wind tunnel test data of different train tests; processing to obtain the load of the test model under the action of the wind tunnel test section airflow; converting a force vector and a torque vector under a balance coordinate system into a force vector and a torque vector under a test model body shafting and a force vector and a torque vector under a wind tunnel airflow shafting through conversion of a coordinate axis system; obtaining a force coefficient vector and a torque coefficient vector under a shaft system of the test model body and a force coefficient vector and a torque coefficient vector under a shaft system of wind tunnel airflow; a curve of aerodynamic force changing along with the angle of attack and a curve of torque coefficient changing along with the angle of attack of the test model are obtained through fitting with a local weighted linear regression method.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel force measurement test, and in particular relates to a wind tunnel continuous force measurement test method. Background Art

[0002] Wind tunnel force test is an aerodynamic test conducted in a wind tunnel. It mainly measures the aerodynamic force of the airflow on the aircraft test model or its components by installing a test model in the wind tunnel test section and a force test balance in the test model. This test is crucial to the development of aircraft, and mainly includes full-machine (missile) force test, half-model force test, component force test, external force test, hinge torque test, etc. In the development process of aircraft, wind tunnel force test is the test type with the highest proportion and the largest test volume, accounting for about 60%~70% of all wind tunnel tests in the model development process.

[0003] Continuous force measurement test means that under the condition of stable wind tunnel flow field (Mach number, total pressure, total temperature, etc.), the attitude angle of the test model changes continuously at a fixed speed (generally less than 0.5° per second), and the data acquisition system continuously collects flow field information and force balance output strain to obtain aerodynamic data of the test model during the entire attitude angle change process. In contrast, step force measurement test means that under the condition of stable wind tunnel flow field, the attitude angle of the test model changes stepwise in a given sequence, and the data acquisition system collects the flow field information and force balance output strain of the test model under a given attitude angle sequence.

[0004] Compared with the step force test which can only obtain aerodynamic data at a given attitude angle, the continuous force test can obtain aerodynamic data of the test model during the entire process from the initial angle of attack / sideslip angle to the final angle of attack / sideslip angle. The data obtained by the continuous force test is dense and detailed, and can obtain more accurate aerodynamic characteristics (such as maximum lift-to-drag ratio, critical angle of attack, etc.). It is also more conducive to obtaining or discovering abnormal data during the change of the model's attitude angle. Figure 1 shown.

[0005] However, unlike the step test, which collects flow field data and balance strain data after judging the flow field (Mach number, total pressure, etc.) is stable at each attitude angle, in the continuous force measurement test, after judging the flow field at the starting attitude angle to be stable, the test model starts to move continuously at a fixed speed to the final attitude angle. During the movement of the model attitude angle, the wind tunnel flow field may exceed the given error band. In general, the Mach number control accuracy of the step force measurement test is required to reach ±0.001, and the Mach number control accuracy of the continuous force measurement test is required to reach ±0.002.

[0006] When the flow field Mach number is greater than 0.7, especially in the transonic stage, the flow field changes dramatically after being disturbed as the model attitude angle changes, especially when the model attitude angle passes "zero" or the model attitude angle is large. When the model attitude angle passes "zero", the overall blockage of the model changes from gradually decreasing to gradually increasing, and the corresponding wind tunnel compressor speed or front chamber total pressure also changes from speed reduction / pressure reduction to speed increase / pressure increase. When the model attitude angle is large, the blockage is greater and the flow separation is more obvious. Therefore, this also poses a higher challenge to flow field control. The current continuous force measurement test method cannot meet the flow field Mach number control accuracy of the same level as the step force measurement test during the entire process of the model attitude angle change after the Mach number is greater than 0.7, especially in the transonic stage, which has an adverse effect on the accuracy of the test data. Summary of the invention

[0007] The present invention aims to solve the problem that in the prior art, when the Mach number is large (Mach number above 0.7, especially in the transonic stage), the flow field Mach number control accuracy cannot reach the same level as the step force measurement test during the entire process of the model attitude angle change, and cannot even meet the Mach number control accuracy requirement of the continuous force measurement test. A wind tunnel continuous force measurement test method is proposed.

[0008] To achieve the above object, the present invention is implemented through the following technical solutions: A wind tunnel continuous force measurement test method comprises the following steps: S1. Install the wind tunnel test support system, force test balance, and test model in the wind tunnel to complete the test preparation; S2. Conduct a windless test, measure the attitude angle of the test model through an angle sensor, obtain the deadweight value of the test model at different attitude angles through a force test balance, and obtain windless test data; S3. Start the wind tunnel and adjust the compressor speed so that the Mach number, total pressure and total temperature of the flow field in the model area of ​​the wind tunnel test section reach the target values; S4. Conduct wind tests and collect wind tunnel test data for different vehicle tests; S5. Based on the wind tunnel test data obtained in step S4, check whether there is test data with a Mach number exceeding the error band, and remove the test data with a Mach number exceeding the error band in the test vehicle; S6. According to the windless test data obtained in step S2, the load of the test model under the action of the airflow in the wind tunnel test section is obtained by processing; S7. By means of coordinate axis conversion, the force vector and moment vector in the balance coordinate system are converted into the force vector and moment vector in the test model axis system and the force vector and moment vector in the wind tunnel airflow axis system; S8. Perform dimensionless processing on the force vector and moment vector through the flow field data collected during the test process to obtain the force coefficient vector and moment coefficient vector under the axis system of the test model and the force coefficient vector and moment coefficient vector under the axis system of the wind tunnel airflow; S9. With the angle of attack of the model attitude angle in the test results as the x-axis, the force coefficient vector and the moment coefficient vector under the test model body axis system obtained in step S8, and the force coefficient vector and the moment coefficient vector under the wind tunnel airflow axis system as the y-axis, respectively, the aerodynamic force curve varying with the angle of attack and the moment coefficient curve varying with the angle of attack of the test model are fitted by the local weighted linear regression method.

[0009] Furthermore, the test preparation work in step S1 includes installation and debugging of test equipment, installation and calibration of angle sensors, inspection and debugging of attitude angle control system, inspection and debugging of flow field control system, surface treatment of test model, zero position adjustment of test model, measurement of installation angle of test model and force test balance, and inspection and testing of data acquisition system.

[0010] Furthermore, the specific implementation method of step S4 includes the following steps: S4.1. Start the attitude angle control system and adjust the test model's angle of attack and sideslip angle to the initial state; S4.2. The flow field control system closes the loop to adjust the total flow pressure and Mach number of the test section to reach the target value; S4.3. The data acquisition system starts to collect the flow field data, angle sensor data and total model load measured by the force test balance of this train; S4.4. The attitude angle control system controls the test model to start moving toward the next angle of attack target according to the given angle of attack step sequence, while the flow field control system continuously adjusts the Mach number of the test section flow field to stabilize it within the error band; S4.5. The test model determines in real time during the motion whether the flow field Mach number is within the error band. When the model attitude angle reaches the target value, if the flow field Mach number control accuracy meets the requirements, repeat step S4.4; S4.6. If the flow field Mach number control accuracy does not meet the requirements, the test model attitude angle stops moving, and waits for the flow field control system to adjust the flow field Mach number until the flow field Mach number control accuracy is stable within the error band, and then repeats step S4.4; S4.7. After completing all the angle of attack sequences in this train, the data acquisition system stops collecting data, and the test model attitude angle returns to zero, and the test of this train ends; S4.8. Start the next test train and repeat steps S4.1 to S4.7 until all test trains of the current test model state are completed and the test ends. The test train of the current test model state refers to the test train without changing the test model conditions under the current test model state.

[0011] Furthermore, the expression of the load of the test model under the action of the airflow in the wind tunnel test section obtained in step S6 is: ; in, is the weight of the test model at the i-th attitude angle, is the total load of the test model at the i-th attitude angle measured by the force test balance under wind test conditions , is the load on the test model at the i-th attitude angle subjected to the airflow in the wind tunnel test section.

[0012] Furthermore, the specific implementation method of step S7 includes the following steps: S7.1. Set the force test balance to the test model coordinate system to satisfy the following relationship: ; in, , , are the pitch, yaw and roll installation angles between the test model and the force test balance, which are obtained during the test preparation process in step S1. To measure the force test balance to the test model coordinates, Force test balance Axis coordinates, Force test balance Axis coordinates, Force test balance Axis coordinates; S7.2. Force vectors about the test model body axis system and the moment vector of the test model body axis system The force vector from the dynamometer test balance and the moment vector of the force test balance After conversion, the relationship is as follows: ; in, The force coordinates from the force test balance to the test model; When the centering position of the force test balance coincides with the position of the test model torque reference point, the following formula is obtained: ; in, is the moment coordinate from the force test balance to the test model; When the centering position of the force test balance does not coincide with the position of the test model torque reference point, the following formula is obtained: ; in, Indicates the distance between the test model torque reference point and the centering position of the force test balance in three directions; ; in, To express the distance between the test model torque reference point and the centering position of the force test balance in the x direction, To express the distance between the test model torque reference point and the centering position of the force test balance in the y direction, It represents the distance between the test model torque reference point and the centering position of the force test balance in the z direction; S7.3. Place the test model body under the axis system and Convert to the force vector in the wind axis system Torque vector in the wind axis system , we get the following relationship: ; ; in, is the Euler rotation matrix of the force coordinate system from the test model body axis system to the wind axis system, is the Euler rotation matrix of the moment coordinate system from the test model body axis system to the wind axis system; The relationship between the Euler rotation matrix of the test model body axis system and the wind axis system is as follows: ; in, is the Euler rotation matrix from the test model body axis to the wind axis, is the Euler rotation matrix from the wind axis to the test model axis, is the angle of attack of the test model axis relative to the wind tunnel flow, is the sideslip angle of the test model axis relative to the wind tunnel flow.

[0013] Furthermore, the specific implementation method of step S8 includes the following steps: S8.1. Set the force coefficients for the test model axis system. and the moment coefficient of the test model axis system The following relationship is satisfied: ; ; Where S is the reference area of ​​the test model, L is the wing span of the test model, b represents the reference chord length or average aerodynamic chord length of the wing of the test model, is the dynamic pressure of wind tunnel flow field; ; in, is the Mach number of the wind tunnel flow field, is the static pressure of the wind tunnel flow field; The expression of the Mach number of the wind tunnel flow field is: ; ; in, for and The correction amount is the specific calibration relationship for each test section of each wind tunnel, and are the total pressure and static pressure of the flow field, respectively, which are collected by the flow field acquisition system during the test. is the reference Mach number of the wind tunnel chamber; The expression of static pressure in wind tunnel flow field is: ; S8.2. Set the force coefficients for the wind axis The moment coefficient of the wind shaft system The following relationship is satisfied: ; .

[0014] Beneficial effects of the present invention: The present invention discloses a wind tunnel continuous force measurement test method, which solves the problem of low Mach number control accuracy when the Mach number is large (Mach number above 0.7, especially in the transonic stage) in a continuous measurement test.

[0015] The wind tunnel continuous force measurement test method described in the present invention fully integrates the advantages of high density of continuous force measurement data and high precision of Mach number control in step tests, obtains more comprehensive aerodynamic data while maintaining better Mach number control precision, and provides more accurate and detailed test data support for aircraft development. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a flow chart of a wind tunnel continuous force measurement test method according to the present invention; Figure 2 It is the comparison curve between the continuous force measurement test and the step force measurement test; Figure 3 This is a flow chart of the wind test of the present invention; Figure 4 This is a comparison chart of the Mach number control accuracy obtained by the present invention and the prior art. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical solution and advantages of the present invention more clear, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention, that is, the specific embodiments described are only part of the embodiments of the present invention, rather than all of the specific embodiments. The components of the specific embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations, and the present invention can also have other embodiments.

[0018] Therefore, the following detailed description of the specific embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents the selected specific embodiments of the present invention. Based on the specific embodiments of the present invention, all other specific embodiments obtained by those skilled in the art without making creative work are within the scope of protection of the present invention.

[0019] In order to further understand the content, features and effects of the present invention, the following specific implementation methods are given as examples, and the attached Figure 1 -Attached Figure 4 The detailed instructions are as follows:

[0020] Embodiment 1: A wind tunnel continuous force measurement test method comprises the following steps: S1. Install the wind tunnel test support system, force test balance, and test model in the wind tunnel to complete the test preparation; Furthermore, the test preparation work in step S1 includes installation and debugging of the test equipment, installation and calibration of the angle sensor, inspection and debugging of the attitude angle control system, inspection and debugging of the flow field control system, surface treatment of the test model, zero position adjustment of the test model, measurement of the installation angle of the test model and the force test balance, and inspection and testing of the data acquisition system; Furthermore, the calibration of the angle sensor means that after the angle sensor is installed in the model body, the inclination sensor is placed on the model reference platform, the model is adjusted to different attitude angles through the attitude angle control system and the output values ​​of the inclination sensor and the angle sensor are recorded, and finally the conversion relationship between the angle sensor and the inclination sensor is obtained by fitting, thus completing the calibration of the angle sensor; S2. Conduct a windless test, measure the attitude angle of the test model through an angle sensor, obtain the deadweight value of the test model at different attitude angles through a force test balance, and obtain windless test data; S3. Start the wind tunnel and adjust the compressor speed so that the Mach number, total pressure and total temperature of the flow field in the model area of ​​the wind tunnel test section reach the target values; S4. Conduct wind tests and collect wind tunnel test data for different vehicle tests; Furthermore, the specific implementation method of step S4 includes the following steps: S4.1. Start the attitude angle control system and adjust the test model's angle of attack and sideslip angle to the initial state; S4.2. The flow field control system closes the loop to adjust the total flow pressure and Mach number of the test section to reach the target value; Furthermore, the error band of total pressure is ±100 Pa, and the error band of Mach number is ±0.001; S4.3. The data acquisition system starts to collect the flow field data, angle sensor data and total model load measured by the force test balance of this train; Furthermore, the flow field data of this train includes the total pressure P 0 , static pressure P ct ; S4.4. The attitude angle control system controls the test model to start moving toward the next angle of attack target according to the given angle of attack step sequence, while the flow field control system continuously adjusts the Mach number of the test section flow field to stabilize it within the error band; Furthermore, the step angle interval of the angle of attack step sequence is no greater than 0.5°; the error band is ±0.001; S4.5. The test model determines in real time during the motion whether the flow field Mach number is within the error band. When the model attitude angle reaches the target value, if the flow field Mach number control accuracy meets the requirements, repeat step S4.4; S4.6. If the flow field Mach number control accuracy does not meet the requirements, the test model attitude angle stops moving, and waits for the flow field control system to adjust the flow field Mach number until the flow field Mach number control accuracy is stable within the error band, and then repeats step S4.4; S4.7. After completing all the angle of attack sequences in this train, the data acquisition system stops collecting data, and the test model attitude angle returns to zero, and the test of this train ends; S4.8. Start the next test train and repeat steps S4.1 to S4.7 until all test trains of the current test model state are completed and the test ends. The test train of the current test model state refers to the test train without changing the test model conditions under the current test model state.

[0021] S5. Based on the wind tunnel test data obtained in step S4, check whether there is test data with a Mach number exceeding the error band, and remove the test data with a Mach number exceeding the error band in the test vehicle; S6. According to the windless test data obtained in step S2, the load of the test model under the action of the airflow in the wind tunnel test section is obtained by processing; Furthermore, the expression of the load of the test model under the action of the airflow in the wind tunnel test section obtained in step S6 is: ; in, is the weight of the test model at the i-th attitude angle, is the total load of the test model at the i-th attitude angle measured by the force test balance under wind test conditions , is the load on the test model under the action of the airflow in the wind tunnel test section at the i-th attitude angle; S7. By means of coordinate axis conversion, the force vector and moment vector in the balance coordinate system are converted into the force vector and moment vector in the test model axis system and the force vector and moment vector in the wind tunnel airflow axis system; Furthermore, the specific implementation method of step S7 includes the following steps: S7.1. Set the force test balance to the test model coordinate system to satisfy the following relationship: ; in, , , are the pitch, yaw and roll installation angles between the test model and the force test balance, which are obtained during the test preparation process in step S1. To measure the force test balance to the test model coordinates, Force test balance Axis coordinates, Force test balance Axis coordinates, Force test balance Axis coordinates; S7.2. Force vectors about the test model body axis system and the moment vector of the test model body axis system The force vector from the dynamometer test balance and the moment vector of the force test balance After conversion, the relationship is as follows: ; in, The force coordinates from the force test balance to the test model; When the centering position of the force test balance coincides with the position of the test model torque reference point, the following formula is obtained: ; in, is the moment coordinate from the force test balance to the test model; When the centering position of the force test balance does not coincide with the position of the test model torque reference point, the following formula is obtained: ; in, Indicates the distance between the test model torque reference point and the centering position of the force test balance in three directions; ; ; ; ; ; in, To express the distance between the test model torque reference point and the centering position of the force test balance in the x direction, To express the distance between the test model torque reference point and the centering position of the force test balance in the y direction, It represents the distance between the test model torque reference point and the centering position of the force test balance in the z direction; S7.3. Place the test model body under the axis system and Convert to the force vector in the wind axis system Torque vector in the wind axis system , we get the following relationship: ; ; in, is the Euler rotation matrix of the force coordinate system from the test model body axis system to the wind axis system, is the Euler rotation matrix of the moment coordinate system from the test model body axis system to the wind axis system; The relationship between the Euler rotation matrix of the test model body axis system and the wind axis system is as follows: ; in, is the Euler rotation matrix from the test model body axis to the wind axis, is the Euler rotation matrix from the wind axis to the test model axis, is the angle of attack of the test model axis relative to the wind tunnel flow, is the sideslip angle of the test model axis relative to the wind tunnel flow; ; .

[0022] S8. Perform dimensionless processing on the force vector and moment vector through the flow field data collected during the test process to obtain the force coefficient vector and moment coefficient vector under the axis system of the test model and the force coefficient vector and moment coefficient vector under the axis system of the wind tunnel airflow; Furthermore, the specific implementation method of step S8 includes the following steps: S8.1. Set the force coefficients for the test model axis system. and the moment coefficient of the test model axis system The following relationship is satisfied: ; ; Where S is the reference area of ​​the test model, L is the wing span of the test model, b represents the reference chord length or average aerodynamic chord length of the wing of the test model, is the dynamic pressure of wind tunnel flow field; ; ; ; in, is the Mach number of the wind tunnel flow field, is the static pressure of the wind tunnel flow field; The expression of the Mach number of the wind tunnel flow field is: ; ; in, for and The correction amount is the specific calibration relationship for each test section of each wind tunnel, and are the total pressure and static pressure of the flow field, respectively, which are collected by the flow field acquisition system during the test. is the reference Mach number of the wind tunnel chamber; The expression of static pressure in wind tunnel flow field is: ; S8.2. Set the force coefficients for the wind axis The moment coefficient of the wind shaft system The following relationship is satisfied: ; ; ; .

[0023] S9. With the angle of attack of the model attitude angle in the test results as the x-axis, the force coefficient vector and the moment coefficient vector under the test model body axis system obtained in step S8, and the force coefficient vector and the moment coefficient vector under the wind tunnel airflow axis system as the y-axis, respectively, the aerodynamic force curve varying with the angle of attack and the moment coefficient curve varying with the angle of attack of the test model are fitted by the local weighted linear regression method.

[0024] It should be noted that relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0025] Although the present application has been described above with reference to specific embodiments, various modifications may be made thereto and parts thereof may be replaced with equivalents without departing from the scope of the present application. In particular, as long as there is no structural conflict, the various features in the specific embodiments disclosed in the present application may be used in combination with each other in any manner, and the fact that these combinations are not exhaustively described in this specification is only for the sake of omitting space and saving resources. Therefore, the present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A wind tunnel continuous force measurement test method, characterized in that: The steps include: S1. Install the wind tunnel test support system, force test balance, and test model in the wind tunnel to complete the test preparation; S2. Conduct a windless test, measure the attitude angle of the test model through an angle sensor, obtain the deadweight value of the test model at different attitude angles through a force test balance, and obtain windless test data; S3. Start the wind tunnel and adjust the compressor speed so that the Mach number, total pressure and total temperature of the flow field in the model area of ​​the wind tunnel test section reach the target values; S4. Conduct wind tests and collect wind tunnel test data for different vehicle tests; S5. Based on the wind tunnel test data obtained in step S4, check whether there is test data with a Mach number exceeding the error band, and remove the test data with a Mach number exceeding the error band in the test vehicle; S6. According to the windless test data obtained in step S2, the load of the test model under the action of the airflow in the wind tunnel test section is obtained by processing; S7. By means of coordinate axis conversion, the force vector and moment vector in the balance coordinate system are converted into the force vector and moment vector in the test model axis system and the force vector and moment vector in the wind tunnel airflow axis system; S8. Perform dimensionless processing on the force vector and moment vector through the flow field data collected during the test process to obtain the force coefficient vector and moment coefficient vector under the axis system of the test model and the force coefficient vector and moment coefficient vector under the axis system of the wind tunnel airflow; S9. With the angle of attack of the model attitude angle in the test results as the x-axis, the force coefficient vector and the moment coefficient vector under the test model body axis system obtained in step S8, and the force coefficient vector and the moment coefficient vector under the wind tunnel airflow axis system as the y-axis, respectively, the aerodynamic force curve varying with the angle of attack and the moment coefficient curve varying with the angle of attack of the test model are fitted by the local weighted linear regression method.

2. A wind tunnel continuous force measurement test method according to claim 1, characterized in that: The test preparation work in step S1 includes the installation and debugging of the test equipment, the installation and calibration of the angle sensor, the inspection and debugging of the attitude angle control system, the inspection and debugging of the flow field control system, the surface treatment of the test model, the zero position adjustment of the test model, the measurement of the installation angle of the test model and the force test balance, and the inspection and testing of the data acquisition system.

3. A wind tunnel continuous force measurement test method according to claim 2, characterized in that: The specific implementation method of step S4 includes the following steps: S4.

1. Start the attitude angle control system and adjust the test model's angle of attack and sideslip angle to the initial state; S4.

2. The flow field control system closes the loop to adjust the total flow pressure and Mach number of the test section to reach the target value; S4.

3. The data acquisition system starts to collect the flow field data, angle sensor data and total model load measured by the force test balance of this train; S4.

4. The attitude angle control system controls the test model to start moving toward the next angle of attack target according to the given angle of attack step sequence, while the flow field control system continuously adjusts the Mach number of the test section flow field to stabilize it within the error band; S4.

5. The test model determines in real time during the motion whether the flow field Mach number is within the error band. When the model attitude angle reaches the target value, if the flow field Mach number control accuracy meets the requirements, repeat step S4.4; S4.

6. If the flow field Mach number control accuracy does not meet the requirements, the test model attitude angle stops moving, and waits for the flow field control system to adjust the flow field Mach number until the flow field Mach number control accuracy is stable within the error band, and then repeats step S4.4; S4.

7. After completing all the angle of attack sequences in this train, the data acquisition system stops collecting data, and the test model attitude angle returns to zero, and the test of this train ends; S4.

8. Start the next test train and repeat steps S4.1 to S4.7 until all test trains of the current test model state are completed and the test ends. The test train of the current test model state refers to the test train without changing the test model conditions under the current test model state.

4. A wind tunnel continuous force measurement test method according to claim 3, characterized in that: The expression of the load of the test model under the action of the airflow in the wind tunnel test section obtained in step S6 is: ； in, is the weight of the test model at the i-th attitude angle, is the total load of the test model at the i-th attitude angle measured by the force test balance under wind test conditions , is the load on the test model at the i-th attitude angle subjected to the airflow in the wind tunnel test section.

5. A wind tunnel continuous force measurement test method according to claim 4, characterized in that: The specific implementation method of step S7 includes the following steps: S7.

1. Set the force test balance to the test model coordinate system to satisfy the following relationship: ； in, , , are the pitch, yaw and roll installation angles between the test model and the force test balance, which are obtained during the test preparation process in step S1. To measure the force test balance to the test model coordinates, Force test balance Axis coordinates, Force test balance Axis coordinates, Force test balance Axis coordinates; S7.

2. Force vectors about the test model body axis system and the moment vector of the test model body axis system The force vector from the dynamometer test balance and the moment vector of the force test balance After conversion, the relationship is as follows: ； in, The force coordinates from the force test balance to the test model; When the centering position of the force test balance coincides with the position of the test model torque reference point, the following formula is obtained: ； in, is the moment coordinate from the force test balance to the test model; When the centering position of the force test balance does not coincide with the position of the test model torque reference point, the following formula is obtained: ； in, Indicates the distance between the test model torque reference point and the centering position of the force test balance in three directions; ； in, To express the distance between the test model torque reference point and the centering position of the force test balance in the x direction, To express the distance between the test model torque reference point and the centering position of the force test balance in the y direction, It represents the distance between the test model torque reference point and the centering position of the force test balance in the z direction; S7.

3. Place the test model body under the axis system and Convert to the force vector in the wind axis system Torque vector in the wind axis system , and we get the following relationship: ； ； in, is the Euler rotation matrix of the force coordinate system from the test model body axis system to the wind axis system, is the Euler rotation matrix of the moment coordinate system from the test model body axis system to the wind axis system; The relationship between the Euler rotation matrix of the test model body axis system and the wind axis system is as follows: ； in, is the Euler rotation matrix from the test model body axis to the wind axis, is the Euler rotation matrix from the wind axis to the test model axis, is the angle of attack of the test model axis relative to the wind tunnel flow, is the sideslip angle of the test model axis relative to the wind tunnel flow.

6. A wind tunnel continuous force measurement test method according to claim 5, characterized in that: The specific implementation method of step S8 includes the following steps: S8.

1. Set the force coefficients for the test model axis system. and the moment coefficient of the test model axis system The following relationship is satisfied: ； ； Where S is the reference area of ​​the test model, L is the wing span of the test model, b represents the reference chord length or average aerodynamic chord length of the wing of the test model, is the dynamic pressure of wind tunnel flow field; ； in, is the Mach number of the wind tunnel flow field, is the static pressure of the wind tunnel flow field; The expression of the Mach number of the wind tunnel flow field is: ； ； in, for and The correction amount is the specific calibration relationship for each test section of each wind tunnel, and are the total pressure and static pressure of the flow field, respectively, which are collected by the flow field acquisition system during the test. is the reference Mach number of the wind tunnel chamber; The expression of static pressure in wind tunnel flow field is: ； S8.

2. Set the force coefficients for the wind axis The moment coefficient of the wind shaft system The following relationship is satisfied: ； 。

Images