CN113324726B - Control surface dynamic aerodynamic wind tunnel test device and method - Google Patents

Abstract

The invention provides a control surface dynamic aerodynamic wind tunnel test device and a control surface dynamic aerodynamic wind tunnel test method, wherein a dynamic data acquisition system is used for acquiring a control surface aerodynamic signal output by an integrated control surface balance and a rudder deflection angle simulation signal output by a rudder deflection angle measurement device; based on the control surface aerodynamic force signal, applying a balance formula to obtain time domain data of each component aerodynamic load; obtaining time domain data containing rudder deflection angles and rudder deflection angle speeds based on the rudder deflection angle time domain data; extracting time domain data of each model main body state within the stay time, and extracting time domain data of a uniform speed section under the condition of forward and reverse rotation of a control surface to obtain two groups of repeated test data under each model main body state; carrying out pneumatic load averaging on each group of repeated test data according to the rudder deflection angle; and subtracting the no-wind test data processing result from the blowing test data processing result to obtain the control surface dynamic aerodynamic force data corresponding to the rudder deflection angle in the process that the control surface is positively and negatively rotated at the preset wind tunnel test rudder deflection angle speed under each model body state.

Description

Device and method for dynamic aerodynamic wind tunnel test of rudder surface

technical field

The invention belongs to the technical field of wind tunnel testing, in particular to a dynamic aerodynamic wind tunnel testing device and method for a rudder surface.

Background technique

When the aircraft maneuvers rapidly, the rudder surface deflects violently, and the flow around the rudder surface shows strong unsteadiness. At this time, the aerodynamic performance must be different from the static hinge moment measured by the conventional rudder surface hinge moment wind tunnel test method. This difference It may cause abnormal hinge torque or even cause the rudder shaft to break. In order to evaluate the difference in aerodynamic characteristics caused by the unsteady effect caused by the dynamic deflection of the rudder surface, it is necessary to provide a dynamic aerodynamic wind tunnel test method for the rudder surface, carry out ground wind tunnel test simulation, and obtain the unsteady aerodynamic characteristics of the rudder surface. Provide a basis for aircraft rudder surface design and simulation.

SUMMARY OF THE INVENTION

In order to overcome the deficiencies in the prior art, the inventor has carried out determined research and provided a rudder surface dynamic aerodynamic wind tunnel test device and method, aiming at the unsteady effect caused by the dynamic deflection of the aircraft rudder surface, the ground wind tunnel test is carried out Simulation, using the dynamic balance to measure the aerodynamic force of the rudder surface during the deflection process of the rudder surface, obtain the unsteady aerodynamic characteristics of the rudder surface, and provide a basis for the design and simulation of the aircraft rudder surface.

The technical scheme provided by the invention is as follows:

In the first aspect, a rudder surface dynamic aerodynamic wind tunnel test device includes a rudder surface deflection system, a rudder deflection angle measuring device, an integrated rudder surface balance, an aircraft model main body, and a dynamic data acquisition system, and the rudder surface deflection system and The main body of the aircraft model is fixedly connected, including the servo motor and the transmission module. The output shaft of the servo motor is fixedly connected with the transmission module, and the transmission module is fixedly connected with the rudder shaft. Do reciprocating motion at a predetermined deflection angular velocity between two rudder deflection angle positions;

The rudder deflection measuring device is fixedly connected with the rudder shaft, and is used to measure the rudder deflection angle in real time, and output the rudder deflection angle analog signal to the dynamic data acquisition system in real time;

The integrated rudder surface balance has the shape of the rudder surface, performs the deflection function of the rudder, and has a built-in balance for real-time output of the aerodynamic signal of the rudder surface to the dynamic data acquisition system;

The main body of the aircraft model is placed in the wind tunnel test section through a support, the rudder deflection system and the rudder deflection angle measuring device are placed inside the main body of the aircraft model, and one or more integrated rudder balances are installed on the aircraft model to form a complete aircraft model;

The dynamic data acquisition system is used for synchronously collecting the rudder surface aerodynamic signal output by the integrated rudder surface balance 5 and the rudder deflection angle analog signal output by the rudder deflection angle measuring device.

In the second aspect, a dynamic aerodynamic wind tunnel test method for a rudder surface includes a test operation part and a data processing part:

Test operation part:

Step 1-1: The main body of the aircraft model is placed in the wind tunnel test section at an angle of attack of 0°, and the integrated rudder surface balance is located at the position of the rudder deflection angle of 0°;

Step 1-2: The dynamic data acquisition system starts to collect the rudder surface aerodynamic signal output by the integrated rudder surface balance and the rudder deflection angle analog signal output by the rudder deflection angle measuring device, and starts the next step after collecting the initial zero signal of the integrated rudder surface balance ;

Step 1-3: After the wind tunnel is started and the flow field is stable, the main body of the aircraft model and the integrated rudder balance start to move at the same time; Move to the next model body state again, stay time T, until the last model body state, return to the initial model body state after the time T; the action of the integrated rudder surface balance 5 is: move from 0° rudder angle position Go to the predetermined rudder angle position a, and then perform N times of reciprocating motion between the predetermined rudder angle position a and another predetermined rudder angle position b in the form of predetermined rudder surface reciprocating motion, and then return from the predetermined rudder angle position a 0° rudder angle position;

Steps 1-4: After the main body of the aircraft model and the balance of the integrated rudder surface are completed, the wind tunnel is shut down, and the data collection is stopped after collecting the last zero signal of the balance, and the wind tunnel test of one vehicle is completed to obtain the blowing test data;

Step 1-5: When the wind tunnel is not blowing, follow steps 1-1 to 1-4 to obtain the no-wind test data;

Data processing part:

Step 2-1: Remove the initial zero and last zero of the aerodynamic signal of the rudder surface, and apply the balance formula to obtain the time domain data of each component of the aerodynamic load;

Step 2-2: Calculate the rudder deflection angular velocity based on the time domain data of the rudder deflection angle, and obtain the time domain data including the rudder deflection angle and the rudder deflection angular velocity;

Step 2-3: Correspond the aerodynamic load time-domain data with the time-domain data of rudder deflection angle and rudder deflection angular velocity, and extract the time-domain data within the residence time T of each model main body state;

Step 2-4: For the time-domain data of each model main body state, extract the time-domain data of the constant velocity section of the rudder deflection angular velocity in the predetermined wind tunnel test under the forward rotation and reverse rotation of the rudder surface respectively, and obtain the time domain data of each model main body state Two groups of repeated test data;

Step 2-5: Perform aerodynamic load averaging according to rudder deflection angle for each group of repeated test data;

Step 2-6: According to steps 2-1 to 2-5, use the same rudder deflection angle sequence to process the blowing test data and the no-wind test data respectively, subtract the processing result of the blowing test data from the no-wind test data processing result to obtain The dynamic aerodynamic force data of the rudder surface corresponding to the rudder deflection angle during the forward rotation and reverse rotation of the rudder surface at a predetermined wind tunnel test rudder deflection angular velocity in each model main state of the aircraft.

A kind of rudder surface dynamic aerodynamic wind tunnel test device and method provided according to the present invention have the following beneficial effects:

(1) According to a kind of rudder surface dynamic aerodynamic wind tunnel test device and method provided by the present invention, aiming at the unsteady effect caused by the dynamic deflection of the aircraft rudder surface, the ground wind tunnel test simulation is carried out, and the dynamic balance is used in the rudder surface deflection process Measuring the aerodynamic force of the rudder surface and obtaining the unsteady aerodynamic characteristics of the rudder surface provides a new idea for the study of the unsteady aerodynamic characteristics of the rudder surface;

(2) According to a kind of rudder surface dynamic aerodynamic wind tunnel test device and method provided by the present invention, it is possible to complete multiple rudder surface reciprocating motions of a plurality of model main body states as much as possible in a vehicle wind tunnel test, while ensuring Before the wind tunnel is shut down, the aircraft model and the integrated rudder surface will return to the initial state after completing the action, which reduces the impact of impact loads that may occur during the start and stop of the wind tunnel;

(3) According to a kind of rudder surface dynamic aerodynamic force wind tunnel test device and method provided by the present invention, it is suitable for the static state of rudder surface under different rudder deflection angles, or the test of the rudder surface aerodynamic force in the deflection process with different speeds .

Description of drawings

Fig. 1 is a schematic structural view of a rudder surface dynamic aerodynamic wind tunnel test device of the present invention.

Explanation of reference numbers

1- Aircraft model main body; 2- Servo motor; 3- Transmission module; 4- Rudder deflection angle measuring device; 5- Integrated rudder surface balance.

Detailed ways

The following describes the present invention in detail, and the features and advantages of the present invention will become more clear and definite along with these descriptions.

The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise indicated.

In order to evaluate the difference in aerodynamic characteristics due to the unsteady effect caused by the dynamic deflection of the rudder surface, it is necessary to carry out ground wind tunnel test simulation, and measure the aerodynamic force of the rudder surface during the deflection process of the rudder surface. The details are as follows.

According to a first aspect of the present invention, as shown in Figure 1, a kind of rudder surface dynamic aerodynamic wind tunnel test device is provided, comprising rudder surface deflection system, rudder deflection angle measuring device 4, integrated rudder surface balance 5, aircraft model The main body 1 and the dynamic data acquisition system, the rudder surface deflection system is fixedly connected with the aircraft model main body 1, including the servo motor 2 and the transmission module 3, the output shaft of the servo motor 2 is connected with the transmission module 3, and the transmission module 3 is connected with the rudder shaft Fixed connection, used to drive one or more rudder surfaces to complete the following actions: the rudder surface is stationary at a predetermined rudder deflection angle position, or the rudder surface reciprocates at a predetermined deflection angular velocity between two predetermined rudder deflection angle positions;

The rudder deflection measuring device 4 is fixedly connected with the rudder shaft, and is used to measure the rudder deflection angle in real time, and output the rudder deflection angle analog signal to the dynamic data acquisition system in real time;

The integrated rudder surface balance 5 has the shape of the rudder surface, and performs the deflection function of the rudder, and has a built-in three-component or five-component balance, which is used to output the aerodynamic force signal of the rudder surface to the dynamic data acquisition system in real time;

The aircraft model main body 1 is placed in the wind tunnel test section by a support, the rudder surface deflection system and the rudder deflection angle measuring device 4 are placed inside the aircraft model main body 1, and one or more integrated rudder surface balances 5 are installed on the aircraft model , forming a complete aircraft model;

The dynamic data collection system is used for synchronously collecting the rudder surface aerodynamic signal output by the integrated rudder surface balance 5 and the rudder deflection angle analog signal output by the rudder deflection angle measuring device 4 .

In the present invention, the rudder surface deflection system also includes a servo control system, the servo control system is used to control the operation of the servo motor, so that the rudder surface moves from the rudder deflection angle position of 0° to the predetermined rudder deflection angle position a during the test, Then do N reciprocating motions between the predetermined rudder deflection angle position a and another predetermined rudder deflection angle position b in the form of predetermined rudder surface reciprocating motions, and then return to the 0° rudder deflection angle position from the predetermined rudder deflection angle position a; wherein , N>mn, N is the number of reciprocating movements of the integrated rudder surface balance in one trip, m is the number of main states of the model in a wind tunnel test for one trip, n is the reciprocating movement of the rudder surface in each main state of the model times.

Further, the servo control system is used to control the operation of the servo motor so that the reciprocating motion of the rudder surface is in the form: the rudder surface starts from the predetermined rudder deflection angle position a, starts to accelerate with a predetermined angular acceleration, and accelerates to the predetermined wind tunnel test rudder deflection angle After the speed, deflect at a constant speed, then start to decelerate with a predetermined angular acceleration, and stop at another predetermined rudder deflection angle position b; then start from the predetermined rudder deflection angle position b, start reverse acceleration with a predetermined angular acceleration, and accelerate to the predetermined wind tunnel test After the rudder deflection angular velocity, it deflects at a uniform speed, then starts to decelerate with a predetermined angular acceleration, returns to the predetermined rudder deflection angle position a and stops, and completes a reciprocating motion.

In the present invention, the wind tunnel test device also includes a model main body state control system, which is used to control the movement of the support, so that the action form of the aircraft model main body is: move to the first model main body state, and then move again after a dwell time T Go to the next model main body state, stay time T, until the last model main body state, return to the initial model main body state after staying time T.

其中ω_WT为风洞试验舵偏角速度，ω_∞为飞行器真实舵偏角速度，d_WT为风洞试验模型参考长度，d_∞为飞行器参考长度，V_WT为风洞试验来流速度，V_∞为飞行器典型飞行状态下的来流速度。In the present invention, the wind tunnel test device also includes a dynamic data processing system, the dynamic data processing system is used to determine the angular velocity of the test rudder, and the angular velocity of the test rudder is determined according to the following formula:

where ω _WT is the angular velocity of the rudder in the wind tunnel test, ω _∞ is the real rudder angular velocity of the aircraft, d _WT is the reference length of the wind tunnel test model, d _∞ is the reference length of the aircraft, V _WT is the incoming flow velocity in the wind tunnel test, V _∞ is the incoming velocity of the aircraft under typical flight conditions.

In the present invention, the dynamic data processing system is also used to obtain the dynamic aerodynamic force result of the rudder surface according to the data collected by the dynamic data acquisition system, in a specific way:

Remove the initial zero and last zero of the aerodynamic signal of the rudder surface, and apply the balance formula to obtain the time-domain data of each component of the aerodynamic load;

Calculate the rudder deflection angular velocity based on the time domain data of the rudder deflection angle, and obtain the time domain data including the rudder deflection angle and the rudder deflection angular velocity;

The aerodynamic load time domain data is corresponding to the rudder deflection angle and rudder deflection angular velocity time domain data, and the time domain data within the residence time T of the main body state of the model are extracted one by one;

For a period of time domain data of each model main body state, based on the rudder deflection angular velocity, the time domain data of the constant speed section of the test rudder deflection angular velocity under the forward rotation and reverse rotation of the rudder surface are respectively extracted, and the time domain data of each model main body state are obtained Two sets of repeated test data, each set of test data consists of n segments of time-domain data including time, rudder deflection angle, and aerodynamic load of each component;

Perform aerodynamic load averaging according to the rudder deflection angle for each group of repeated test data: define a rudder deflection angle sequence, the range of the rudder deflection angle of this sequence is not greater than the rudder deflection angle range of any period of time domain data in the group of repeated test data; Each period of time domain data takes the rudder deflection angle as the independent variable and the aerodynamic load as the dependent variable, interpolates the aerodynamic load components to the rudder deflection angle sequence one by one, and obtains a set of repeated test data of the aerodynamic load data under the rudder deflection angle sequence; Do the arithmetic mean for each aerodynamic load component to obtain the aerodynamic load data of the rudder deflection angle sequence;

Use the same rudder deflection angle sequence to process the blowing test data and the no-wind test data respectively, subtract the processing results of the no-wind test data from the processing results of the blowing test data, and obtain the test rudder deflection angle of the rudder surface of the aircraft in each model main state The dynamic aerodynamic force data of the rudder surface corresponding to the rudder deflection angle during the speed forward and reverse rotation.

According to a second aspect of the present invention, a dynamic aerodynamic wind tunnel test method for rudder surfaces is provided, including a test operation part and a data processing part:

Test operation part:

Step 1-1: The main body of the aircraft model is placed in the wind tunnel test section with an attack angle of 0°, and the integrated rudder surface balance is located at the rudder deflection angle of 0°.

Considering the impact loads that may occur during the start-stop process of the wind tunnel, before the start of the wind tunnel, the main body of the aircraft model is placed in the wind tunnel test section at an angle of attack of 0°, and the integrated rudder surface balance is located at the position of the rudder deflection angle; the wind tunnel The main body of the aircraft model and the rudder surface will start to move after the start-up flow field is stable. After all measurements are completed, the main body of the aircraft model and the rudder surface should return to the initial state before the wind tunnel is shut down.

Step 1-2: The dynamic data acquisition system starts to collect the rudder surface aerodynamic signal output by the integrated rudder surface balance and the rudder deflection angle analog signal output by the rudder deflection angle measuring device, and starts the next step after collecting the initial zero signal of the integrated rudder surface balance . Preferably, the sampling frequency of the dynamic data acquisition system is determined according to the angular velocity of the rudder in the wind tunnel test, so that the interval between the maximum rudder angles of adjacent sampling points is 0.5° to 1°, for example, the angular velocity of the test rudder is 1200°/ When s, the sampling frequency is 1200Hz, and the maximum rudder angle interval between adjacent sampling points is 1°.

Step 1-3: After the wind tunnel is started and the flow field is stable, the main body of the aircraft model and the integrated rudder balance start to move at the same time. The action of the main body of the aircraft model is: move to the first model main body state, after a stay time T, move to the next model main body state again, stay time T, until the last model main body state, and return to the initial model main body state after the stay time T . The action of the integrated rudder surface balance 5 is: move from the 0° rudder deflection angle position to the predetermined rudder deflection angle position a, and then move between the predetermined rudder deflection angle position a and another predetermined rudder deflection angle position in the form of predetermined rudder surface reciprocating motion. Do N times of reciprocating motion between b, and then return to the 0° rudder angle position from the predetermined rudder angle position a. The residence time of the main body of each model is T>nt, t is the time required for one reciprocating movement of the integrated rudder surface balance. The number of reciprocating movements of the integrated rudder surface balance in one trip is N>mn, m is the number of model main states in a wind tunnel test for one trip, and n is the number of times the rudder surface completes reciprocating movements in each model main state; the actual test Among them, m, n and T need to be comprehensively determined according to t and the maximum running time of the wind tunnel.

Most of the wind tunnel tests use temporary wind tunnels. For temporary wind tunnels, each time the wind tunnel is opened, there is a maximum running time. In order to complete as many reciprocating movements of the rudder surface as possible in the main state of multiple models in one wind tunnel test, and ensure that the wind tunnel is closed before the wind tunnel is closed The main body of the aircraft model and the integrated rudder balance are completed and returned to the initial state, and the above-mentioned blowing test steps are set. In the dynamic test, it is usually necessary to carry out repetitive tests. Therefore, in the main state of each model, the rudder surface completes n times of reciprocating motions. The larger n is, the better. Generally, n=6~8.

In the present invention, due to the scale ratio of the model, the wind tunnel test rudder deflection angular velocity is often several times larger than the real rudder deflection velocity of the aircraft, and the rudder surface deflection system needs a certain amount of time to drive the rudder surface to accelerate from a static state to a predetermined wind tunnel test rudder deflection. Angular velocity, it also takes time for the rudder surface to decelerate from the predetermined wind tunnel test rudder angular velocity state to a static state, and the greater the rudder angular velocity, the longer the acceleration and deceleration time is required. Therefore, the form of reciprocating motion of the rudder surface is: the rudder surface starts from the predetermined rudder deflection angle position a, starts to accelerate with a predetermined angular acceleration, accelerates to a predetermined wind tunnel test rudder deflection angular velocity, deflects at a uniform speed, and then starts to decelerate with a predetermined angular acceleration, Stop at another predetermined rudder deflection angle position b; then start from the predetermined rudder deflection angle position b, start reverse acceleration with a predetermined angular acceleration, accelerate to the predetermined wind tunnel test rudder deflection angular velocity, deflect at a uniform speed, and then accelerate at a predetermined angular acceleration Start to decelerate, get back to the predetermined rudder deflection angle position a and stop, and complete a reciprocating motion.

In practical applications, the range of the predetermined rudder deflection angle needs to be adjusted according to the test conditions, the predetermined wind tunnel test rudder deflection angular velocity, and the range of the rudder deflection angle to be tested, so as to ensure that the aerodynamic load on the rudder surface does not exceed the deflection of the rudder surface under the test conditions. The maximum load limit of the system and the integrated rudder surface balance, and at the same time ensure that the rudder surface can reach the predetermined wind tunnel test rudder angular velocity within the range of the rudder deflection angle to be tested. For example, the requirements of the wind tunnel test for the dynamic aerodynamic force measurement of the rudder surface of an aircraft model are: the test rudder deflection angle ranges from 0° to 30°, and the predetermined wind tunnel test rudder deflection velocity is 1200°/s. If the rudder surface deflection system drives the rudder surface to deflect 13° within the time period from stationary acceleration to the predetermined wind tunnel test rudder angular velocity, that is, the rudder surface acceleration and deceleration processes require 13° rudder surface deflection space respectively, you can set The predetermined rudder deflection angle position a is -13°, and the predetermined rudder deflection angle position b is 43°, which can ensure that the rudder surface can reach the predetermined wind tunnel test rudder deflection velocity within the range of the rudder deflection angle to be tested; Under these conditions, whether the aerodynamic load on the rudder surface within the range of -13°～43° rudder deflection exceeds the maximum load limit of the rudder surface deflection system and the integrated rudder surface balance; if it does not meet the maximum load limit requirements, it needs to be appropriately reduced The rudder deflection range to be tested or reduce the test rudder deflection speed.

其中ω_WT为风洞试验舵偏角速度，ω_∞为飞行器真实舵偏角速度，d_WT为风洞试验模型参考长度，d_∞为飞行器参考长度，V_WT为风洞试验来流速度，V_∞为飞行器典型飞行状态下的来流速度。In the dynamic aerodynamic wind tunnel test of the rudder surface, in addition to satisfying the similarity criteria such as geometric similarity and Mach number similarity, the scale model also needs to meet the Strouhal number similarity criterion, that is, the deflection angular velocity of the rudder surface needs to be adjusted according to the model scale . The angular velocity of the rudder in the wind tunnel test is determined according to the following formula:

where ω _WT is the angular velocity of the rudder in the wind tunnel test, ω _∞ is the real rudder angular velocity of the aircraft, d _WT is the reference length of the wind tunnel test model, d _∞ is the reference length of the aircraft, V _WT is the incoming flow velocity in the wind tunnel test, V _∞ is the incoming velocity of the aircraft under typical flight conditions.

Steps 1-4: After the main body of the aircraft model and the balance of the integrated rudder surface are completed, the wind tunnel is shut down, and the data collection is stopped after collecting the last zero signal of the balance, and the wind tunnel test of one vehicle is completed to obtain the blowing test data;

Step 1-5: When the wind tunnel is not blowing, follow steps 1-1 to 1-4 to obtain the no-wind test data.

Data processing part:

Step 2-1: Remove the initial zero and last zero of the aerodynamic signal of the rudder surface, and apply the balance formula to obtain the time-domain data of each component of the aerodynamic load.

For example, when the integrated rudder surface balance 5 has a built-in three-component balance, the time-domain data of each component aerodynamic load includes the time-domain data of the three-component aerodynamic load of normal force, hinge moment and rudder root bending moment.

Step 2-2: Calculate the rudder deflection angular velocity based on the time domain data of the rudder deflection angle, and obtain the time domain data including the rudder deflection angle and the rudder deflection angular velocity.

Step 2-3: Correspond the aerodynamic load time-domain data with the time-domain data of rudder deflection angle and rudder deflection angular velocity, and extract the time-domain data within the residence time T of each model main body state.

Specifically, the specific method for extracting the time-domain data within the residence time T of each model main body state is: method 1, extracting according to the loads that have significant differences in different model main body states. For example, when the rudder surface moves to 0° rudder deflection angle, the normal force of the rudder surface has obvious difference under different attack angle states of the main body state of the model. Conversely, according to the rudder surface movement to 0° rudder deflection angle The normal force difference, which distinguishes the preset model body state. Method 2, an attitude sensor can be installed on the main body of the model, and the state signal of the main body of the model can be recorded synchronously through the dynamic data acquisition system.

Step 2-4: For the time-domain data of the main state of each model, based on the rudder deflection angular velocity, extract the time-domain data of the constant velocity section of the rudder deflection angular velocity in the predetermined wind tunnel test under the forward rotation and reverse rotation of the rudder surface respectively, and obtain Two sets of repeated test data in the main state of each model, each set of test data consists of n segments of time domain data including time, rudder deflection angle, and aerodynamic load of each component.

Step 2-5: Perform aerodynamic load averaging according to the rudder deflection angle for each group of repeated test data, the method is as follows: define a rudder deflection angle sequence, and the range of the rudder deflection angle of this sequence is not greater than any period of time domain in this group of repeated test data The rudder deflection angle range of the data; for each period of time domain data, with the rudder deflection angle as the independent variable and the aerodynamic load as the dependent variable, the aerodynamic load components are interpolated into the rudder deflection angle sequence one by one to obtain a set of the rudder deflection angle sequence Repeat the test data for the aerodynamic load data; do the arithmetic mean for each aerodynamic load component to obtain the aerodynamic load data of the rudder deflection angle sequence.

The specific example is as follows: use the integrated rudder surface balance with built-in three-component balance to measure the dynamic aerodynamic force of the rudder surface of a certain model. The wind tunnel test rudder deflection angular velocity is 1200°/s, the test sampling frequency is 1200Hz, and the test rudder deflection angle ranges from 0° to 10°. A set of aerodynamic load data was extracted when the rudder surface rotated forward at a rudder angular velocity of 1200°/s including three repeated tests, and each test data included time, rudder deflection angle, normal force, hinge moment and rudder root bending moment. The rudder deflection angle sequence (unit ° omitted) of the three sections of test data are {-1.15, -0.15, 0.85, 1.85, ..., 9.85, 10.85}, {-0.91, 0.09, 1.09, 2.09, ..., 10.09, 11.09} , {-1.06,-0.06,0.94,1.94,...,9.94,10.94}. A new sequence of rudder deflection angles {0.00, 1.00, 2.00, 3.00,...,10.00} can be defined, and the rudder deflection angle range of this rudder deflection angle sequence is not greater than the rudder deflection angle range of any period of time domain data in the group of repeated test data. For each piece of aerodynamic load data, the aerodynamic load is interpolated into a new sequence with the rudder deflection angle as the independent variable and the normal force, hinge moment, and rudder root bending moment as the dependent variables respectively. For each rudder deflection angle position in the new sequence, the aerodynamic load data of three repeated tests are arithmetically averaged to obtain the average aerodynamic load data of the new sequence.

Step 2-6: According to steps 2-1 to 2-5, use the same rudder deflection angle sequence in step 2-5 to process the blowing test data and the no-wind test data respectively, and subtract the no-wind test data processing results from the blowing test data As a result of the test data processing, the dynamic aerodynamic force data of the rudder surface corresponding to the rudder deflection angle in the process of forward rotation and reverse rotation of the rudder surface at a predetermined wind tunnel test rudder deflection angular velocity under each model main state of the aircraft is obtained.

The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions should not be construed as limiting the present invention. Those skilled in the art understand that without departing from the spirit and scope of the present invention, various equivalent replacements, modifications or improvements can be made to the technical solutions and implementations of the present invention, all of which fall within the scope of the present invention. The protection scope of the present invention shall be determined by the appended claims.

The content that is not described in detail in the description of the present invention belongs to the well-known technology of those skilled in the art.

Claims (10)

1. A control surface dynamic aerodynamic wind tunnel test device is characterized by comprising a control surface deflection system, a control surface deflection angle measuring device (4), an integrated control surface balance (5), an aircraft model main body (1), a dynamic data acquisition system and a dynamic data processing system;

the control surface deflection system is fixedly connected with the aircraft model body (1) and comprises a servo motor (2) and a transmission module (3), an output shaft of the servo motor (2) is fixedly connected with the transmission module (3), and the transmission module (3) is fixedly connected with a control shaft and used for driving the control surface to be static at a preset control deflection angle position or to reciprocate at a preset deflection angle speed between two preset control deflection angle positions;

the rudder deflection angle measuring device (4) is fixedly connected with the rudder shaft and is used for measuring the rudder deflection angle in real time and outputting a rudder deflection angle simulation signal to the dynamic data acquisition system in real time;

the integrated control surface balance (5) has the appearance of a control surface, performs the deflection function of the rudder, is internally provided with a balance and is used for outputting a control surface aerodynamic force signal to a dynamic data acquisition system in real time;

the aircraft model main body (1) is arranged in a wind tunnel test section through a support piece, the control surface deflection system and the rudder deflection angle measuring device (4) are arranged in the aircraft model main body (1), and one or more integrated control surface balances (5) are arranged on the aircraft model to form a complete aircraft model;

the dynamic data acquisition system is used for synchronously acquiring a control surface aerodynamic force signal output by the integrated control surface balance (5) and a rudder deflection angle simulation signal output by the rudder deflection angle measurement device;

the dynamic data processing system is used for obtaining a control surface dynamic aerodynamic force result according to data collected by the dynamic data collecting system, and comprises: removing initial zero and final zero of the aerodynamic force signal of the control surface, and applying a balance formula to obtain time domain data of each component aerodynamic load;

calculating the rudder deflection angle speed based on the rudder deflection angle time domain data to obtain time domain data containing the rudder deflection angle and the rudder deflection angle speed;

corresponding the pneumatic load time domain data with rudder deflection angle and rudder deflection angle speed time domain data, and extracting the time domain data within the model main body state retention time T one by one;

respectively extracting time domain data of a uniform speed section of the test rudder deflection angle speed under the conditions of forward rotation and reverse rotation of a control surface for a section of time domain data of each model main body state based on the rudder deflection angle speed to obtain two groups of repeated test data under each model main body state, wherein each group of test data comprises at least one section of time domain data containing time, rudder deflection angle and each component of pneumatic load;

carrying out pneumatic load averaging on each group of repeated test data according to the rudder deflection angle;

and respectively processing the blowing test data and the calm test data by using the same rudder deflection angle sequence, and subtracting the calm test data processing result from the blowing test data processing result to obtain the control surface dynamic aerodynamic force data corresponding to the rudder deflection angle in the process that the control surface of the aircraft rotates forwards and backwards at the test rudder deflection angle speed under each model body state.

2. The rudder surface dynamic aerodynamic wind tunnel test device according to claim 1, wherein the rudder surface deflection system further comprises a servo control system, the servo control system is used for controlling a servo motor to operate, so that the rudder surface moves from a 0 ° rudder deflection angle position to a predetermined rudder deflection angle position a during test, then performs N times of reciprocating motion between the predetermined rudder deflection angle position a and another predetermined rudder deflection angle position b in a predetermined rudder surface reciprocating motion mode, and then returns to the 0 ° rudder deflection angle position from the predetermined rudder deflection angle position a; and N is more than mn, N is the reciprocating motion frequency of the integrated control surface balance in a train number, m is the number of model main body states in a train number wind tunnel test, and N is the frequency of the reciprocating motion of the control surface in each model main body state.

3. The rudder surface dynamic aerodynamic wind tunnel test device according to claim 1, wherein the servo control system is used for controlling a servo motor to operate, so that the reciprocating motion mode of the rudder surface is as follows: starting from a preset rudder deflection angle position a, starting acceleration at a preset angular acceleration, accelerating to a preset wind tunnel test rudder deflection angle speed, deflecting at a constant speed, starting deceleration at the preset angular acceleration, and stopping at another preset rudder deflection angle position b; starting from the preset rudder deflection angle position b, starting reverse acceleration with preset angular acceleration, accelerating to the preset wind tunnel test rudder deflection angle speed, deflecting at a constant speed, starting deceleration with the preset angular acceleration, returning to the preset rudder deflection angle position a, stopping, and completing one reciprocating motion.

4. The wind tunnel test device for the dynamic aerodynamic force of the control surface according to claim 1 is characterized by further comprising a model body state control system, wherein the model body state control system is used for controlling the movement of the support piece, so that the action form of the aircraft model body is as follows: and (4) acting to a first model main body state, after the stay time T, acting to a next model main body state again, staying for the time T until the last model main body state, and returning to the initial model main body state after the stay time T.

5. The rudder surface dynamic aerodynamic wind tunnel test device according to claim 1, wherein the dynamic data processing system is configured to determine a test rudder deflection angular velocity, the test rudder deflection angular velocity being determined according to the following formula:

wherein ω is _WT Is windHole test rudder deflection angular velocity, omega _∞ For the true rudder angle speed of the aircraft, d _WT Reference length for wind tunnel test model, d _∞ For aircraft reference length, V _WT For wind tunnel testing of incoming velocity, V _∞ The incoming flow velocity of the aircraft in a typical flight state.

6. A control surface dynamic aerodynamic wind tunnel test method is characterized by comprising a test operation part and a data processing part:

test operation part:

step 1-1: the aircraft model main body is arranged in a wind tunnel test section at an attack angle of 0 degree, and the integrated control surface balance is positioned at a rudder deflection angle position of 0 degree;

step 1-2: the dynamic data acquisition system starts to acquire a control surface aerodynamic force signal output by the integrated control surface balance and a rudder deflection angle analog signal output by the rudder deflection angle measurement device, and starts the next step after acquiring an initial zero signal of the integrated control surface balance;

step 1-3: starting the wind tunnel, and after the flow field is stable, simultaneously starting the action of the aircraft model main body and the integrated control surface balance; the actions of the aircraft model main body are as follows: the model is operated to the first model main body state, after the stay time T, the model is operated to the next model main body state again, the stay time T is up to the last model main body state, and the initial model main body state is returned after the stay time T; the action of the integrated control surface balance is as follows: moving from the 0-degree rudder deflection angle position to a preset rudder deflection angle position a, then performing N times of reciprocating motion between the preset rudder deflection angle position a and another preset rudder deflection angle position b in a preset control surface reciprocating motion mode, and then returning to the 0-degree rudder deflection angle position from the preset rudder deflection angle position a;

step 1-4: after the action of the aircraft model main body and the integrated control surface balance is finished, the vehicle is shut down in a wind tunnel, data collection is stopped after a balance end zero signal is collected, a train number wind tunnel test is finished, and blowing test data are obtained;

step 1-5: under the condition that the wind tunnel does not blow, obtaining the windless test data according to the steps 1-1 to 1-4;

a data processing section:

step 2-1: removing initial zero and final zero of the aerodynamic force signal of the control surface, and applying a balance formula to obtain time domain data of each component aerodynamic load;

step 2-2: calculating the rudder deflection angle speed based on the rudder deflection angle time domain data to obtain time domain data comprising the rudder deflection angle and the rudder deflection angle speed;

step 2-3: corresponding the pneumatic load time domain data with rudder deflection angle and rudder deflection angle speed time domain data, and extracting time domain data within the stay time T of each model main body state;

step 2-4: respectively extracting time domain data of a constant speed section of a preset wind tunnel test rudder deflection angle speed under the situations of forward rotation and reverse rotation of the control surface from the time domain data of each model main body state to obtain two groups of repeated test data under each model main body state;

step 2-5: carrying out pneumatic load averaging on each group of repeated test data according to the rudder deflection angle;

step 2-6: and according to the steps 2-1 to 2-5, respectively processing the blowing test data and the no-wind test data by using the same rudder deflection angle sequence, and subtracting the no-wind test data processing result from the blowing test data processing result to obtain the control plane dynamic aerodynamic force data corresponding to the rudder deflection angle in the process that the control plane of the aircraft rotates forwards and backwards at the preset wind tunnel test rudder deflection angle speed in each model body state.

7. The control surface dynamic aerodynamic wind tunnel test method according to claim 6, characterized in that in the steps 1-3, the state retention time T of each model main body is more than nt, and T is the time required by one reciprocating motion of the integrated control surface balance; the reciprocating times N of the integrated control surface balance in one train are more than mn, m is the number of model main body states in a wind tunnel test of the train, and N is the times of the control surface completing reciprocating motion in each model main body state.

8. The control surface dynamic aerodynamic wind tunnel test method according to claim 6, characterized in that in the steps 1-3, the reciprocating motion form of the control surface is as follows: starting from a preset rudder deflection angle position a, starting acceleration at a preset angular acceleration, accelerating to a preset wind tunnel test rudder deflection angle speed, deflecting at a constant speed, starting deceleration at the preset angular acceleration, and stopping at another preset rudder deflection angle position b; starting from the preset rudder deflection angle position b, starting reverse acceleration with preset angular acceleration, accelerating to the preset wind tunnel test rudder deflection angle speed, deflecting at a constant speed, starting deceleration with the preset angular acceleration, returning to the preset rudder deflection angle position a, stopping, and completing one reciprocating motion.

9. The rudder surface dynamic aerodynamic wind tunnel test method according to claim 8, wherein the wind tunnel test rudder deflection angle speed is determined according to the following formula:

wherein ω is _WT For wind tunnel testing of rudder deflection angular velocity, omega _∞ For the true rudder angle speed of the aircraft, d _WT Reference length for wind tunnel test model, d _∞ For aircraft reference length, V _WT For wind tunnel testing of incoming velocity, V _∞ The incoming flow velocity of the aircraft in a typical flight state.

10. The rudder surface dynamic aerodynamic wind tunnel test method according to claim 6, wherein in the step 2-5, the method for performing aerodynamic load averaging according to rudder deflection angle on each group of repeated test data is as follows: defining a rudder deflection angle sequence, wherein the range of the rudder deflection angle of the sequence is not larger than that of any section of time domain data in the repeated test data; for each segment of time domain data, interpolating the pneumatic load components to the rudder deflection angle sequence one by taking the rudder deflection angle as an independent variable and taking the pneumatic load as a dependent variable to obtain a group of pneumatic load data repeated test data under the rudder deflection angle sequence; and performing arithmetic mean on each pneumatic load component to obtain pneumatic load data of the rudder deflection angle sequence.

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