Method for Obtaining Continuous Wind Tunnel Aerodynamic Load Based on Online Monitoring of Balance Zero Point

Abstract

The present invention proposes a method for obtaining continuous wind tunnel aerodynamic loads based on on-line monitoring of the balance zero point, belonging to the technical field of aerodynamic wind tunnel tests in aviation and aerospace. First, a wind tunnel balance calibration formula and a balance working formula are generated; secondly, the wind tunnel balance response outputs and time point data under multiple test conditions and the wind tunnel balance zero point under the windless condition are collected; the standard aerodynamic loads are obtained by applying the balance zero point, the wind tunnel balance response output of the last condition and the balance working formula; the real-time zero points of the wind tunnel balance under each condition are calculated by applying the standard aerodynamic loads, the wind tunnel balance response outputs under multiple test conditions and the balance calibration formula; finally, between the real-time zero points of the wind tunnel balance under every two test conditions, the real-time zero points of the wind tunnel balance under the test conditions are linearly interpolated according to the time series, and the aerodynamic loads acting on the scaled model of the aircraft are obtained by applying the wind tunnel balance working formula. The problem of being unable to apply to the alternating temperature and pressure environment during the operation of a continuous wind tunnel is solved.

Description

Technical Field

[0001] This application relates to a method for obtaining aerodynamic loads, and particularly to a method for obtaining continuous wind tunnel aerodynamic loads based on on-line monitoring of balance zero points, belonging to the technical field of aerodynamic wind tunnel tests in aviation and aerospace. Background Art

[0002] Aerodynamic performance is one of the key factors for evaluating the success or failure of aircraft model development. Precise aerodynamic design and accurate aerodynamic prediction are the primary conditions for ensuring excellent aerodynamic performance of aircraft. At present, wind tunnel tests are the main means for accurate aerodynamic prediction and are directly involved in the aerodynamic design process of aircraft. In wind tunnel tests, a wind tunnel balance directly senses the aerodynamic loads acting on the scaled model of the aircraft: the zero point of the wind tunnel balance under the no-wind condition and the response output of the wind tunnel balance under the wind tunnel blowing condition obtained by acquisition are used, and the aerodynamic loads acting on the scaled model of the aircraft are calculated by using the working formula of the wind tunnel balance.

[0003] At present, production wind tunnels mainly include two types: continuous wind tunnels and blowdown wind tunnels. The continuous wind tunnel is driven by a fan compressor system to make the air flow move in the wind tunnel loop, and the running time is up to several hours; during the operation of the wind tunnel, the wind tunnel balance is always in a complex environment of alternating temperature and alternating pressure, which seriously affects the zero point of the wind tunnel balance. The blowdown wind tunnel is driven by a pre-compressed high or medium pressure air source or pumped by a vacuum tank to form an air flow, and the running time is short (about one minute), and the zero point of the wind tunnel balance is stable. Therefore, there are great risks and errors in directly applying the zero point of the wind tunnel balance under the no-wind condition to calculate the aerodynamic loads acting on the scaled model of the aircraft in a continuous wind tunnel.

[0004] The existing technical solutions mainly focus on the off-line detection, compensation, and correction methods for the change of the zero point of the wind tunnel balance with temperature and pressure, and cannot fully apply to the complex environment of alternating temperature and pressure during the operation of a continuous wind tunnel. Summary of the Invention

[0005] A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify the key or important parts of the present invention, nor is it intended to limit the scope of the present invention. Its purpose is only to present certain concepts in a simplified form as a prelude to the more detailed description to be discussed later.

[0006] In view of this, to solve the technical problem that the existing technical solutions mainly focus on the off-line detection, compensation, and correction methods for the change of the zero point of the wind tunnel balance with temperature and pressure and cannot fully apply to the complex environment of alternating temperature and pressure during the operation of a continuous wind tunnel, the present invention provides a method for obtaining continuous wind tunnel aerodynamic loads based on on-line monitoring of balance zero points.

[0007] Solution 1: A method for obtaining continuous wind tunnel aerodynamic loads based on online monitoring of the balance zero point, comprising the following steps:

[0008] S1. In the wind tunnel balance calibration stage, generate a wind tunnel balance calibration formula with the wind tunnel balance response output as the dependent variable and a wind tunnel balance working formula with the load as the dependent variable, specifically including the following steps:

[0009] S11. Apply precise six-dimensional force calibration loads to the wind tunnel balance on the balance calibration device according to the known coordinate system and the compiled calibration load table, and simultaneously collect the corresponding response outputs of each component of the wind tunnel balance;

[0010] S12. Apply the regression algorithm of the least squares principle to fit and generate a wind tunnel balance calibration formula with the wind tunnel balance response output as the dependent variable; the calibration formula for each component of the wind tunnel balance with the response output as the dependent variable is:

[0011] ;

[0012] In the formula, n is the number of components of the wind tunnel balance, and i, j, and K are the indices of each component of the wind tunnel balance; R i is the response output of the i-th component of the wind tunnel balance to be fitted and generated; is the zero-load output of the i-th component; is the first-order coefficient of the load of the j-th component on the i-th component; is the second-order square coefficient and cross-term coefficient of the j-th and k-th components on the i-th component; P j and P k are the loads of the j-th and k-th components of the wind tunnel balance;

[0013] S13. Combine the calibration formulas of all components obtained in S12 to generate the calibration formula of the wind tunnel balance:

[0014] ;

[0015] Obtain the wind tunnel balance working formula with the load as the dependent variable through matrix transformation calculation:

[0016] ;

[0017] In the formula, m is the number of coefficient terms in the balance calibration, is the column vector composed of subtracting from each component of the wind tunnel balance , is the square matrix composed of the coefficient terms of each component of the wind tunnel balance , is the column vector composed of the load values of each component of the wind tunnel balance , is a matrix composed of the coefficient terms of each component of the wind tunnel balance and is a matrix composed of the coefficient terms of each component of the wind tunnel balance is a column vector obtained by calculating the load values of each component of the wind tunnel balance and and is a column vector composed of is the inverse matrix of the matrix and is the inverse matrix of the matrix is the matrix multiplied by the matrix to obtain the matrix;

[0018] S2. During the wind tunnel test stage, collect the wind tunnel balance response outputs and time point data under at least two monitored test conditions; before the end of the wind tunnel test, collect the wind tunnel balance response outputs and time point data under the last monitored test condition; and after the end of the wind tunnel test, collect the zero point of the wind tunnel balance under the no-wind condition;

[0019] S3. Based on the zero point of the wind tunnel balance under the no-wind condition, the wind tunnel balance response outputs collected before the end of the wind tunnel test, and the wind tunnel balance working formula generated during the wind tunnel balance calibration stage, linearly interpolate the real-time zero point of the wind tunnel balance under the test conditions in time series, and based on the wind tunnel balance working formula, solve to obtain the aerodynamic loads acting on the scaled model of the aircraft.

[0020] Preferably, S2 specifically includes the following steps:

[0021] S21. Install the wind tunnel balance on the wind tunnel support, install the aircraft model on the wind tunnel balance, collect the initial zero point of the wind tunnel balance, and set the test parameters of the monitored test conditions and the assessment threshold for the over-limit of the aerodynamic loads;

[0022] S22. Start the continuous wind tunnel, drive the wind tunnel to run to the test parameters of the monitored test conditions, and after preheating, collect the wind tunnel balance response outputs and time point data of the first monitored test condition;

[0023] S23. Based on the initial zero point of the wind tunnel balance collected in S21, the wind tunnel balance response outputs collected in S22, and the wind tunnel balance working formula with the load as the dependent variable generated in S1, iteratively solve the aerodynamic loads of the first monitored test condition;

[0024] S24. Run the wind tunnel according to the predetermined blowing test sequence conditions, collect the wind tunnel balance response outputs and time point data under each test condition, run the wind tunnel, drive the wind tunnel to run to the test parameters of the monitored test condition, and collect the wind tunnel balance response outputs and time point data of the monitored test condition;

[0025] S25. Judge whether all the blowing tests are completed. If completed, execute S29; otherwise, execute S26;

[0026] S26. Based on the initial zero point of the wind tunnel balance collected in S21, the response output of the wind tunnel balance collected in S24, and the wind tunnel balance working formula generated by S1 with the load as the dependent variable, iteratively solve and calculate the aerodynamic load of the monitored test condition.

[0027] S27. Calculate the difference between the aerodynamic load solved in S26 and the aerodynamic load of the previous monitored test condition. When the difference is greater than the assessment threshold of the aerodynamic load tolerance set in S21, jump to S29.

[0028] S28. Repeat S24 - S27 until all the working conditions of the predetermined blowing test sequence are completed. Drive the wind tunnel to run to the test parameters of the monitored test condition, and collect the response output and time point data of the wind tunnel balance of the last monitored test condition.

[0029] S29. End of the wind tunnel test: Shut down the wind tunnel and collect the zero point of the wind tunnel balance under the no - wind condition.

[0030] Preferably, S3 specifically includes the following steps:

[0031] S31. Based on the zero point of the wind tunnel balance under the no - wind condition, the response output of the wind tunnel balance of the monitored test condition collected before the end of the wind tunnel test, and the wind tunnel balance working formula, iteratively solve and obtain the standard aerodynamic load of the monitored test condition.

[0032] S32. Based on the standard aerodynamic load of the monitored test condition, the response output of the wind tunnel balance of the monitored test condition collected during the test stage, and the wind tunnel balance calibration formula, solve the real - time zero point of the wind tunnel balance under each monitored test condition.

[0033] S33. Between the real - time zero points of the wind tunnel balance under two adjacent monitored test conditions, linearly interpolate the real - time zero point of the wind tunnel balance under the test condition in time series to obtain the real - time zero point of the wind tunnel balance corresponding to the predetermined blowing test condition.

[0034] S34. Based on the real - time zero point of the wind tunnel balance under the predetermined blowing test condition, the response output of the wind tunnel balance under the test condition, and the wind tunnel balance working formula, iteratively solve and calculate the aerodynamic load under each predetermined blowing test condition.

[0035] Solution 2: An electronic device, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, it implements the steps of the method for obtaining the continuous wind tunnel aerodynamic load based on the online monitoring of the balance zero point in Solution 1.

[0036] Solution 3: A computer - readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it implements the method for obtaining the continuous wind tunnel aerodynamic load based on the online monitoring of the balance zero point in Solution 1.

[0037] The beneficial effects of the present invention are as follows:

[0038] (1) The present invention can accurately capture the real-time zero point of the wind tunnel balance under each blowing test vehicle, thereby improving and ensuring the accuracy of continuous wind tunnel test data;

[0039] (2) The present invention can timely detect test anomalies, shut down the wind tunnel to check for problems, and reduce the number of invalid test vehicles;

[0040] (3) The present invention can reduce the preheating time of the continuous wind tunnel, thereby greatly improving efficiency and reducing costs. Description of the Drawings

[0041] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation of the present application. In the drawings:

[0042] Figure 1 It is a schematic flow diagram of a method for obtaining aerodynamic loads of a continuous wind tunnel based on online monitoring of the balance zero point.

[0043] Figure 2 It is a schematic flow diagram of the S21-S29 process. Detailed Embodiments

[0044] In order to make the technical solutions and advantages in the embodiments of the present application clearer, the following further describes the exemplary embodiments of the present application in detail with reference to the drawings. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than an exhaustive list of all embodiments. It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

[0045] Embodiment 1. Refer to Figure 1 - Figure 2 This embodiment describes a method for obtaining aerodynamic loads of a continuous wind tunnel based on online monitoring of the balance zero point, including the following steps:

[0046] S1. In the wind tunnel balance calibration stage, generate a wind tunnel balance calibration formula with the wind tunnel balance response output as the dependent variable and a wind tunnel balance working formula with the load as the dependent variable, specifically including the following steps:

[0047] S11. Apply precise six-dimensional force calibration loads to the wind tunnel balance on the balance calibration device according to the known coordinate system and the compiled calibration load table, and simultaneously collect the corresponding response outputs of each component of the wind tunnel balance;

[0048] S12. Apply a regression algorithm based on the least squares principle to fit and generate a wind tunnel balance calibration formula with the wind tunnel balance response output as the dependent variable; the calibration formula for each component of the wind tunnel balance with the response output as the dependent variable is:

[0049] ;

[0050] In the formula, n is the number of components of the wind tunnel balance, and i, j, and k are the indices of each component of the wind tunnel balance; R i is the response output of the i-th component of the wind tunnel balance to be fitted and generated; is the zero-load output of the i-th component; is the first-order coefficient of the j-th component load on the i-th component; is the second-order square coefficient and cross-term coefficient of the j-th and k-th components on the i-th component; P j and P k are the loads of the j-th and k-th components of the wind tunnel balance;

[0051] S13. Combine the calibration formulas of all components obtained in S12 to generate the calibration formula of the wind tunnel balance:

[0052] ;

[0053] Calculate and obtain the working formula of the wind tunnel balance with the load as the dependent variable through matrix transformation:

[0054] ;

[0055] In the formula, m is the number of coefficient terms for the balance calibration, is the column vector composed of subtracting from each component of the wind tunnel balance , is the square matrix composed of the coefficient terms of each component of the wind tunnel balance, is the column vector composed of the load values of each component of the wind tunnel balance, is the matrix composed of the coefficient terms of each component of the wind tunnel balance, is the and calculated from the load values of each component of the wind tunnel balance and composed into a column vector, is the inverse matrix of the matrix , is the matrix obtained by multiplying the matrix by the matrix ;

[0056] S2. During the wind tunnel test phase, collect the response output and time point data of the wind tunnel balance under at least two monitored test conditions; before the end of the wind tunnel test, collect the response output and time point data of the wind tunnel balance under the last monitored test condition, and after the end of the wind tunnel test, collect the zero point of the wind tunnel balance under the no-wind condition;

[0057] S21. Wind tunnel test preparation: Install the wind tunnel balance on the wind tunnel support, install the aircraft model on the wind tunnel balance, collect the initial zero point of the wind tunnel balance, and set the test parameters for monitoring the test conditions and the assessment threshold for the over - tolerance of aerodynamic loads;

[0058] S22. Wind tunnel test blowing: Start the continuous wind tunnel, drive the wind tunnel to run to reach the test parameters of the monitored test conditions. After pre - heating for 20 minutes, collect the response output and time - point data of the wind tunnel balance for the first monitored test condition;

[0059] S23. Based on the initial zero point of the wind tunnel balance collected in S21, the response output of the wind tunnel balance collected in S22, and the wind tunnel balance working formula with load as the dependent variable generated in S1, iteratively solve the aerodynamic load for the first monitored test condition;

[0060] S24. Run the wind tunnel according to the predetermined blowing test sequence conditions, collect the response output and time - point data of the wind tunnel balance under each test condition. After the wind tunnel runs for 30 minutes, drive the wind tunnel to run to reach the test parameters of the monitored test conditions, and collect the response output and time - point data of the wind tunnel balance for the monitored test condition;

[0061] S25. Determine whether all blowing tests are completed. If completed, execute S29; otherwise, execute S26;

[0062] S26. Based on the initial zero point of the wind tunnel balance collected in S21, the response output of the wind tunnel balance collected in S24, and the wind tunnel balance working formula with load as the dependent variable generated in S1, iteratively solve the aerodynamic load for the monitored test condition;

[0063] S27. Calculate the difference between the aerodynamic load solved in S26 and the aerodynamic load of the previous monitored test condition. When the difference is greater than the assessment threshold for the over - tolerance of aerodynamic loads set in S21, jump to S29;

[0064] S28. Repeat S24 - S27 until all the predetermined blowing test sequence conditions are completed. Drive the wind tunnel to run to reach the test parameters of the monitored test conditions, and collect the response output and time - point data of the wind tunnel balance for the last monitored test condition;

[0065] S29. Wind tunnel test end: Shut down the wind tunnel and collect the zero point of the wind tunnel balance under the no - wind condition.

[0066] S3. Based on the zero point of the wind tunnel balance under the no - wind condition collected after the wind tunnel test ends, the response output of the wind tunnel balance collected before the wind tunnel test ends, and the wind tunnel balance working formula generated during the wind tunnel balance calibration stage, linearly interpolate the real - time zero point of the wind tunnel balance under the test conditions in time series, and solve to obtain the aerodynamic load acting on the scaled - down model of the aircraft.

[0067] S31. Based on the zero point of the wind tunnel balance under the no-wind condition, the wind tunnel balance response output collected before the end of the wind tunnel test, and the working formula of the wind tunnel balance, iteratively solve to obtain the standard aerodynamic load as the monitored test condition;

[0068] S32. Based on the standard aerodynamic load of the monitored test condition, the wind tunnel balance response output collected during the test stage, and the calibration formula of the wind tunnel balance, solve the real-time zero point of the wind tunnel balance under each monitored test condition;

[0069] S33. Between the real-time zero points of the wind tunnel balance under two adjacent monitored test conditions, linearly interpolate the real-time zero point of the wind tunnel balance under the test condition according to the time series to obtain the real-time zero point of the wind tunnel balance corresponding to the predetermined blowing test condition;

[0070] S34. Based on the real-time zero point of the wind tunnel balance under the predetermined blowing test condition, the wind tunnel balance response output under the test condition, and the working formula of the wind tunnel balance, iteratively solve the aerodynamic load under each predetermined blowing test condition.

[0071] This embodiment further illustrates the present invention by taking a rod-type six-component wind tunnel balance with a diameter of 80 as an example:

[0072] Step 1: In the calibration stage of the wind tunnel balance, generate the calibration formula of the wind tunnel balance with the wind tunnel balance response output as the dependent variable and the working formula of the wind tunnel balance with the load as the dependent variable respectively;

[0073] Step 1-1: Apply accurate six-dimensional force calibration loads to the wind tunnel balance on the balance calibration device according to the known coordinate system and the compiled calibration load table, and simultaneously collect the response outputs of each component of the corresponding wind tunnel balance;

[0074]

[0075] Step 1-2: Apply the regression algorithm using the least squares principle to fit and generate a wind tunnel balance calibration formula matrix with the response output of the wind tunnel balance as the dependent variable. The 80-diameter rod-type wind tunnel balance is a six-component balance, and the wind tunnel balance calibration formula includes 6×27 coefficients;

[0076]

[0077] Step 1-3: Combine the calibration formulas of all components obtained in Step 1-2 to generate the calibration formula matrix of this wind tunnel balance, and then calculate through matrix transformation to obtain the working formula matrix of this wind tunnel balance with the load as the dependent variable. , where is the column vector of the response outputs of each component of the wind tunnel balance, is the square matrix composed of the first-order coefficients in the wind tunnel balance calibration formula, is the column vector composed of the load values of each component of the wind tunnel balance, is the matrix composed of the second-order square coefficients and cross-term coefficients in the wind tunnel balance calibration formula, is the column vector composed of the squared values and cross-multiplied values obtained from the load calculations of each component of the wind tunnel balance, is the inverse matrix of matrix , is matrix multiplied by matrix to obtain the matrix.

[0078] Step 2: During the wind tunnel test phase, collect the response outputs and time point data of the wind tunnel balance under multiple monitored test conditions, and immediately collect the zero point of the wind tunnel balance under the no-wind condition after shutting down the wind tunnel;

[0079] Step 2-1: Use a certain aircraft model in the wind tunnel test. Install the wind tunnel balance on the wind tunnel support, and then install the aircraft model on the wind tunnel balance; set the test parameters of the monitored test conditions to Mach number 0.75, Reynolds number 3 million, angle of attack 10°, and sideslip angle 0°;

[0080] Step 2-2: Start the continuous wind tunnel, drive the wind tunnel to run to reach the test parameters of the monitored test conditions. After preheating for 20 minutes, collect the response output of the wind tunnel balance for the first monitored test condition as U Y监1 =2.4608, U Mz监1 =-1.0468, U Mx监1 =0.5331, U X监1= 1.36, U Z监1 = 1.796 and U My监1 = 1.199, set the acquisition time to 0;

[0081] Step 2-3: Operate the wind tunnel according to the predetermined blowing test sequence conditions, and collect the wind tunnel balance response output and time point data under each test condition. For example, the test parameters of the test condition are Mach number 0.9, Reynolds number 3 million, angle of attack 10°, and sideslip angle 0°. The wind tunnel balance response output is U Y试验 = 3.0515, U Mz试验 = -1.3393, U Mx试验 = 0.6447, U X试验 = 1.7019, U Z试验 = 2.0941 and U My试验 = 1.4281, set the acquisition time to 10; The wind tunnel runs for 30 minutes, drives the wind tunnel to run to reach the test parameters of the monitored test condition, and collects the wind tunnel balance response output of the monitored test condition as U Y监2 = 2.4618, U Mz监2 = -1.0458, U Mx监2 = 0.5321, U X监2 = 1.3614, U Z监2 = 1.7948 and U My监2 = 1.1979, set the acquisition time to 30;

[0082] Step 2-4: Shut down the wind tunnel and immediately collect the wind-off zero point of the wind tunnel balance as U Y停 = 0.099, U Mz停 = 0.1269, U Mx停 = 0.0862, U X停 = -0.1133, U Z停 = 0.631 and U My停 = 0.2468.

[0083] Step 3: Use the aerodynamic load of the last monitored test condition as the standard load, solve the real-time zero point of the wind tunnel balance under each monitored test condition, and then linearly interpolate the real-time zero point of the wind tunnel balance under the test condition in time series between the real-time zero points of the wind tunnel balance under every two adjacent monitored test conditions, and then solve to obtain the aerodynamic load acting on the scaled model of the aircraft.

[0084] Step 3-1: Apply the wind-off zero point of the wind tunnel balance, the wind tunnel balance response output, and the wind tunnel balance working formula matrix with the load as the dependent variable, and iteratively solve to obtain the standard aerodynamic load as Y for the monitored test condition 标 = 2124.6, Mz 标 = -122.4, Mx 标=81.94, X 标 =154.81, Z 标 =261.8 and My 标 =24.41;

[0085] Step Thirty - Two: Apply the standard aerodynamic load of the monitored test condition obtained by the solution and the wind tunnel balance response output collected under the monitored test condition, as well as the wind tunnel balance calibration formula matrix with the wind tunnel balance response output as the dependent variable, to solve the real - time zero point U of the wind tunnel balance under the monitored test condition Y监0 =0.098, U Mz监0 =0.1259, U Mx监0 =0.0872, U X监0 =-0.1147, U Z监0 =0.6322 and U My监0 =0.2479;

[0086] Step Thirty - Three: Between the real - time zero point of the wind tunnel balance under the monitored test condition obtained by the solution and the wind - stopped zero point of the collected wind tunnel balance, apply the time - point data under the collected test condition and the monitored test condition, and linearly interpolate the real - time zero point U of the wind tunnel balance under the test condition according to the time series Y试验0 =0.0983, U Mz试验0 =0.1262, U Mx试验0 =0.0869, U X试验0 =-0.1142, U Z试验0 =0.6318 and U My试验0 =0.2475;

[0087] Step Thirty - Four: Apply the real - time zero point of the wind tunnel balance under the blowing test condition obtained by interpolation and the wind tunnel balance response output collected under the corresponding test condition, as well as the wind tunnel balance working formula matrix with the load as the dependent variable, and iteratively solve the aerodynamic load Y under each predetermined blowing test condition 试验 =2655.74, Mz 试验 =-153.02, Mx 试验 =102.74, X 试验 =193.04, Z 试验 =327.49 and My 试验 =30.39.

[0088] Embodiment 2. The computer device of the present invention may be a device including a processor and a memory, such as a single - chip microcomputer including a central processing unit. And, when the processor executes the computer program stored in the memory, it realizes the steps of the method for obtaining the continuous - type wind tunnel aerodynamic load based on the online monitoring of the balance zero point

[0089] The so-called processor may be a Central Processing Unit (CPU), or may also be other general-purpose processors, Digital Signal Processors (DSPs), Application Specific Integrated Circuits (ASICs), Field-Programmable Gate Arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc.

[0090] The memory may mainly include a program storage area and a data storage area. Among them, the program storage area may store an operating system, application programs required for at least one function (such as a sound playback function, an image playback function, etc.); the data storage area may store data created according to the use of the mobile phone (such as audio data, phone book, etc.). In addition, the memory may include high-speed random access memory and may also include non-volatile memory, such as a hard disk, memory, plug-in hard disk, Smart Media Card (SMC), Secure Digital (SD) card, Flash Card, at least one magnetic disk storage device, flash memory device, or other volatile solid-state storage devices.

[0091] Embodiment 3, Embodiment of Computer-Readable Storage Medium

[0092] The computer-readable storage medium of the present invention may be any form of storage medium readable by the processor of the computer device, including but not limited to non-volatile memory, volatile memory, ferroelectric memory, etc. A computer program is stored on the computer-readable storage medium. When the processor of the computer device reads and executes the computer program stored in the memory, the steps of the above method for obtaining continuous wind tunnel aerodynamic loads based on online monitoring of the balance zero point can be implemented.

[0093] The computer program includes computer program code, which may be in the form of source code, object code, executable file or some intermediate form, etc. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc. It should be noted that the content included in the computer-readable medium may be appropriately increased or decreased according to the requirements of legislation and patent practice within the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the computer-readable medium does not include electrical carrier signals and telecommunication signals.

[0094] Although the present invention has been described based on a limited number of embodiments, those skilled in the art in this technical field will understand, based on the above description, that other embodiments can be conceived within the scope of the present invention thus described. In addition, it should be noted that the language used in this specification is mainly selected for the purpose of readability and teaching, rather than for the purpose of explaining or limiting the subject matter of the present invention. Therefore, many modifications and changes will be obvious to those of ordinary skill in this technical field without departing from the scope and spirit of the appended claims. For the scope of the present invention, the disclosure of the present invention is illustrative rather than restrictive, and the scope of the present invention is defined by the appended claims.

Claims

1. A method for obtaining continuous wind tunnel aerodynamic loads based on on-line monitoring of the balance zero point, characterized in that, Including the following steps: S1. In the wind tunnel balance calibration stage, generate a wind tunnel balance calibration formula with the wind tunnel balance response output as the dependent variable and a wind tunnel balance working formula with the load as the dependent variable, specifically including the following steps: S11. Apply precise six-dimensional force calibration loads to the wind tunnel balance on the balance calibration device according to the known coordinate system and the compiled calibration load table, and simultaneously collect the corresponding response outputs of each component of the wind tunnel balance; S12. Apply the regression algorithm of the least squares principle to fit and generate a wind tunnel balance calibration formula with the wind tunnel balance response output as the dependent variable; the calibration formula for each component of the wind tunnel balance with the response output as the dependent variable is: ； where n is the number of components of the wind tunnel balance, and i, j, and k are the indices of each component of the wind tunnel balance; R i is the response output of the i-th component of the wind tunnel balance to be fitted and generated; is the zero-load output of the i-th component; is the first-order coefficient of the j-th component load on the i-th component; is the second-order square coefficient and cross-term coefficient of the j-th and k-th components on the i-th component; P j and P k are the loads of the j-th and k-th components of the wind tunnel balance; S13. Combine the calibration formulas of all components obtained in S12 to generate the calibration formula of the wind tunnel balance: ； Obtain the wind tunnel balance working formula with the load as the dependent variable of the wind tunnel balance through matrix transformation calculation: ； where m is the number of coefficient terms for balance calibration, is the column vector formed by subtracting from for each component of the wind tunnel balance, is the square matrix composed of the coefficient terms of each component of the wind tunnel balance, is the column vector composed of the load values of each component of the wind tunnel balance, is the matrix composed of the coefficient terms of each component of the wind tunnel balance, is the column vector obtained by calculating the load values of each component of the wind tunnel balance and and is the inverse matrix of matrix is the matrix obtained by multiplying matrix by matrix ;​​​​​ S2. In the wind tunnel test stage, collect the wind tunnel balance response output and time point data under at least two monitored test conditions; before the end of the wind tunnel test, collect the wind tunnel balance response output and time point data under the last monitored test condition; and after the end of the wind tunnel test, collect the zero point of the wind tunnel balance under the no-wind condition; S3. Based on the zero point of the wind tunnel balance under the no-wind condition collected after the end of the wind tunnel test, the wind tunnel balance response output collected before the end of the wind tunnel test, and the wind tunnel balance working formula generated in the wind tunnel balance calibration stage, linearly interpolate the real-time zero point of the wind tunnel balance under the test conditions in time series, and solve to obtain the aerodynamic load acting on the scaled model of the aircraft.

2. The method for obtaining continuous wind tunnel aerodynamic loads based on on-line monitoring of the balance zero point according to claim 1, characterized in that, S2 specifically includes the following steps: S21. Wind tunnel test preparation: Install the wind tunnel balance on the wind tunnel support, install the aircraft model on the wind tunnel balance, collect the initial zero point of the wind tunnel balance, and set the test parameters of the monitored test conditions and the assessment threshold for aerodynamic load overrun; S22. Wind tunnel test blowing: Start the continuous wind tunnel, drive the wind tunnel to run to the test parameters of the monitored test conditions, and after preheating for 20 minutes, collect the wind tunnel balance response output and time point data of the first monitored test condition; S23. Based on the initial zero point of the wind tunnel balance collected in S21, the wind tunnel balance response output collected in S22, and the wind tunnel balance working formula generated in S1 with the load as the dependent variable, iteratively solve the aerodynamic load of the first monitored test condition; S24. Run the wind tunnel according to the predetermined blowing test sequence conditions, collect the wind tunnel balance response output and time point data under each test condition, after the wind tunnel runs for 30 minutes, drive the wind tunnel to run to the test parameters of the monitored test conditions, and collect the wind tunnel balance response output and time point data of the monitored test conditions; S25. Determine whether all blowing tests are completed. If completed, execute S29; otherwise, execute S26; S26. Based on the initial zero point of the wind tunnel balance collected in S21, the wind tunnel balance response output collected in S24, and the wind tunnel balance working formula generated in S1 with the load as the dependent variable, iteratively solve the aerodynamic load of the monitored test conditions; S27. Calculate the difference between the aerodynamic load calculated in S26 and the aerodynamic load of the previous monitored test condition. When the difference is greater than the assessment threshold of the aerodynamic load tolerance set in S21, jump to S29; S28. Repeat S24 - S27 until all the working conditions of the predetermined blowing test sequence are completed. Drive the wind tunnel to run to the test parameters of the monitored test condition, and collect the wind tunnel balance response output and time point data of the last monitored test condition; S29. End of the wind tunnel test: Shut down the wind tunnel and collect the zero point of the wind tunnel balance under the no-wind condition.

3. The method for obtaining continuous wind tunnel aerodynamic loads based on on-line monitoring of the balance zero point according to claim 2, characterized in that, S3 specifically includes the following steps: S31. Based on the zero point of the wind tunnel balance under the no-wind condition, the wind tunnel balance response output of the monitored test condition collected before the end of the wind tunnel test, and the wind tunnel balance working formula, iteratively calculate to obtain the standard aerodynamic load as the monitored test condition; S32. Based on the standard aerodynamic load of the monitored test condition, the wind tunnel balance response output of the monitored test condition collected during the test stage, and the wind tunnel balance calibration formula, calculate the real-time zero point of the wind tunnel balance under each monitored test condition; S33. Linearly interpolate the real-time zero point of the wind tunnel balance under the test condition in time series between the real-time zero points of the wind tunnel balance under two adjacent monitored test conditions to obtain the real-time zero point of the wind tunnel balance corresponding to the predetermined blowing test condition; S34. Based on the real-time zero point of the wind tunnel balance under the predetermined blowing test condition, the wind tunnel balance response output under the test condition, and the wind tunnel balance working formula, iteratively calculate the aerodynamic load under each predetermined blowing test condition.

4. An electronic device, characterized in that, It includes a memory and a processor. The memory stores a computer program. When the processor executes the computer program, it implements the steps of the method for obtaining the continuous wind tunnel aerodynamic load based on the online monitoring of the balance zero point according to any one of claims 1 - 3.

5. A computer-readable storage medium, on which a computer program is stored, characterized in that, When the computer program is executed by the processor, it implements the method for obtaining the continuous wind tunnel aerodynamic load based on the online monitoring of the balance zero point according to any one of claims 1 - 3.

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