CN116659803A - Method for acquiring aerodynamic load of continuous wind tunnel based on balance zero point on-line monitoring - Google Patents
Method for acquiring aerodynamic load of continuous wind tunnel based on balance zero point on-line monitoring Download PDFInfo
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Abstract
The application provides a method for acquiring a continuous wind tunnel aerodynamic load based on balance zero point on-line monitoring, and belongs to the technical field of aerospace aerodynamic wind tunnel tests. Firstly, generating a wind tunnel balance calibration formula and a balance working formula; secondly, acquiring response output and time point data of the wind tunnel balance under a plurality of test working conditions and zero point of the wind tunnel balance under a windless working condition; the wind tunnel balance response output and balance working formulas of the balance zero point and the final working condition are applied to obtain a standard aerodynamic load; the method comprises the steps of calculating real-time zero points of wind tunnel balances under various working conditions by applying standard aerodynamic loads and response output of the wind tunnel balances under various test working conditions and a balance calibration formula; and finally, applying a wind tunnel balance working formula between the wind tunnel balance real-time zero points under each two test working conditions and the wind tunnel balance real-time zero points under the time sequence linear interpolation test working conditions to obtain the aerodynamic load acting on the aircraft scaling model. The method solves the problem that the method is not suitable for alternating temperature and pressure environments during continuous wind tunnel operation.
Description
Technical Field
The application relates to a method for acquiring aerodynamic load, in particular to a method for acquiring continuous wind tunnel aerodynamic load based on balance zero point on-line monitoring, and belongs to the technical field of aerospace aerodynamic wind tunnel tests.
Background art
Aerodynamic performance is one of the key factors in evaluating the development success or failure of aircraft models, and fine aerodynamic design and accurate aerodynamic prediction are the primary conditions for ensuring that an aircraft has superior aerodynamic performance. At present, wind tunnel tests are a main means of aerodynamic force accurate prediction and directly participate in the aerodynamic force design process of an aircraft. In wind tunnel tests, wind tunnel scales directly sense aerodynamic loads acting on an aircraft scaling model: and (3) calculating aerodynamic load on the aircraft scaling model by using the acquired wind balance zero point under the windless working condition and wind balance response output under the wind tunnel blowing working condition and a wind balance working formula.
At present, the production type wind tunnel mainly comprises a continuous wind tunnel and a temporary flushing wind tunnel. The continuous wind tunnel is driven by a fan compressor system to move in a wind tunnel loop, and the running time is as long as a plurality of hours; in the wind tunnel operation process, the wind tunnel balance is always in a complex environment with alternating temperature and alternating pressure, and the zero point of the wind tunnel balance is seriously affected. The temporary flushing wind tunnel is driven by a pre-compressed high and medium pressure air source or pumped by a vacuum tank to form airflow flow, the running time is short (about one minute), and the zero point of the wind tunnel balance is stable. Therefore, when the wind tunnel balance zero point under the windless working condition is directly applied in the continuous wind tunnel, the aerodynamic load on the aircraft scaling model is calculated with great risk and error.
The prior art scheme is mainly based on an off-line detection, compensation and correction method for the change of the zero point of the wind tunnel balance along with the temperature and the pressure, and cannot be completely suitable for a complex environment with alternating temperature and pressure during continuous wind tunnel operation.
Disclosure of Invention
The following presents a simplified summary of the application in order to provide a basic understanding of some aspects of the application. It should be understood that this summary is not an exhaustive overview of the application. It is not intended to identify key or critical elements of the application or to delineate the scope of the application. Its purpose is to present some concepts in a simplified form as a prelude to the more detailed description that is discussed later.
In view of the above, the application provides a method for acquiring the aerodynamic load of a continuous wind tunnel based on online monitoring of the balance zero point, which aims to solve the technical problem that the method for detecting, compensating and correcting the change of the zero point of the offline wind tunnel balance along with the temperature and the pressure in the prior art cannot be fully suitable for the complex environment of alternating temperature and pressure during continuous wind tunnel operation.
The method for acquiring the aerodynamic load of the continuous wind tunnel based on the balance zero point on-line monitoring comprises the following steps:
s1, in a wind tunnel balance calibration stage, generating a wind tunnel balance calibration formula which takes response output of the wind tunnel balance as a dependent variable and a wind tunnel balance working formula which takes load as a dependent variable, wherein the method specifically comprises the following steps of:
s11, applying accurate six-dimensional force calibration load to the wind tunnel balance on the balance calibration device according to a known coordinate system and a compiled calibration load meter, and collecting response output of each component of the corresponding wind tunnel balance;
s12, fitting to generate a wind tunnel balance calibration formula taking wind tunnel balance response output as a dependent variable by applying a regression algorithm of a least square method principle; the calibration formula of each component of the wind tunnel balance with response output as a dependent variable is as follows:
；
wherein n is the component number of the wind tunnel balance, and i, j and K are indexes of components of the wind tunnel balance; r is R i The response output of the ith component of the wind tunnel balance is generated by fitting;is the zero-load output of the i-th component;Is the first order coefficient of the j-th component load to the i-th component;Is the second order square coefficient and cross term coefficient of the j and k components to the i component; p (P) j And P k Is wind tunnel skyThe load of the flat j and k components;
s13, combining the calibration formulas of all the components obtained in the S12 to generate a calibration formula of the wind tunnel balance:
；
obtaining a wind tunnel balance working formula taking load as a dependent variable of the wind tunnel balance through matrix conversion calculation:
；
where m is the number of coefficient terms for balance calibration,is composed of wind tunnel balance components>Minus->Column vectors composed later,/->Is composed of wind tunnel balance components>Matrix of coefficient terms->Is formed by the load value of each component of the wind tunnel balance>Column vectors of composition>Is composed of wind tunnel balance components>Matrix of coefficient terms>Is calculated from the load values of the components of the wind tunnel balance>And->Column vectors of composition>Is a matrix->Inverse matrix of>Is a matrix->And matrix->A matrix obtained by multiplication;
s2, in a wind tunnel test stage, collecting response output and time point data of a wind tunnel balance under at least two monitoring test working conditions; before the wind tunnel test is finished, collecting response output and time point data of a wind tunnel balance under the last monitoring test working condition; after the wind tunnel test is finished, collecting a wind tunnel balance zero point under a windless working condition;
s3, based on a wind tunnel balance zero point under a windless working condition, wind tunnel balance response output acquired before wind tunnel test is finished and a wind tunnel balance working formula generated in a wind tunnel balance level calibration stage, the wind tunnel balance real-time zero point under a time sequence linear interpolation test working condition, and based on the wind tunnel balance working formula, the aerodynamic load acting on the aircraft scaling model is obtained through calculation.
Preferably, S2 specifically comprises the following steps:
s21, installing a wind tunnel balance on a wind tunnel support, installing an aircraft model on the wind tunnel balance, collecting an initial zero point of the wind tunnel balance, and setting a test parameter for monitoring a test working condition and an assessment threshold value for out-of-tolerance aerodynamic load;
s22, starting a continuous wind tunnel, driving the wind tunnel to run to achieve test parameters for monitoring test conditions, and collecting response output and time point data of a wind tunnel balance for monitoring the test conditions after preheating;
s23, iteratively solving aerodynamic load of a first monitoring test working condition based on the initial zero point of the wind tunnel balance acquired in the S21, the response output of the wind tunnel balance acquired in the S22 and a wind tunnel balance working formula which is generated in the S1 and takes the load as a dependent variable;
s24, operating the wind tunnel according to a preset blowing test sequence working condition, collecting wind tunnel balance response output and time point data under each test working condition, operating the wind tunnel, driving the wind tunnel to operate to achieve test parameters of a monitoring test working condition, and collecting wind tunnel balance response output and time point data of the monitoring test working condition;
s25, judging whether all blowing tests are finished, if yes, executing S29, otherwise, executing S26;
s26, iteratively calculating aerodynamic load of a monitoring test working condition based on the initial zero point of the wind tunnel balance acquired in S21, the response output of the wind tunnel balance acquired in S24 and a wind tunnel balance working formula which is generated in S1 and takes load as a dependent variable;
s27, carrying out difference between the aerodynamic load calculated in the step S26 and the aerodynamic load of the previous monitoring test working condition, and jumping to the step S29 when the difference is larger than an assessment threshold value set in the step S21 and the aerodynamic load exceeds the difference;
s28, repeating the steps S24-S27 until the preset blowing test sequence working conditions are all completed, driving the wind tunnel to run to reach test parameters of the monitoring test working conditions, and collecting wind tunnel balance response output and time point data of the final monitoring test working conditions;
s29, wind tunnel test is finished: and closing the wind tunnel, and collecting the zero point of the wind tunnel balance under the windless working condition.
Preferably, S3 specifically comprises the following steps:
s31, iteratively calculating to obtain a standard aerodynamic load serving as a monitoring test working condition based on a wind tunnel balance zero point under a windless working condition, a monitoring test working condition wind tunnel balance response output acquired before a wind tunnel test is ended and a wind tunnel balance working formula;
s32, based on the standard aerodynamic load of the monitoring test working conditions and the response output of the wind tunnel balance and the wind tunnel balance calibration formula of the monitoring test working conditions collected in the test stage, resolving the real-time zero point of the wind tunnel balance under each monitoring test working condition;
s33, linearly interpolating the real-time zero point of the wind tunnel balance under the test working condition according to time sequence between the real-time zero points of the wind tunnel balance under the adjacent two monitoring test working conditions to obtain the real-time zero point of the wind tunnel balance under the preset blowing test working condition;
s34, iteratively calculating aerodynamic load of each preset blowing test working condition based on the real-time zero point of the wind tunnel balance under the preset blowing test working condition, the response output of the wind tunnel balance under the test working condition and the working formula of the wind tunnel balance.
The second scheme is an electronic device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor realizes the first scheme of the method for acquiring the aerodynamic load of the continuous wind tunnel based on the balance zero point on-line monitoring when executing the computer program.
A third aspect is a computer readable storage medium, on which a computer program is stored, where the computer program when executed by a processor implements the method for obtaining a continuous wind tunnel aerodynamic load based on balance zero point online monitoring according to the first aspect.
The beneficial effects of the application are as follows:
(1) The method can accurately capture the real-time zero point of the wind tunnel balance under each blowing test train number, thereby improving and guaranteeing the accuracy of continuous wind tunnel test data;
(2) The application can find out the test abnormality in time, shut down the wind tunnel and examine the problem, reduce the invalid test train number;
(3) The application can reduce the preheating time of the continuous wind tunnel, thereby greatly improving the efficiency and reducing the cost.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute a limitation on the application. In the drawings:
FIG. 1 is a flow chart of a method for acquiring a continuous wind tunnel aerodynamic load based on balance zero point online monitoring.
FIG. 2 is a schematic flow chart of S21-S29.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following detailed description of exemplary embodiments of the present application is provided in conjunction with the accompanying drawings, and it is apparent that the described embodiments are only some embodiments of the present application and not exhaustive of all embodiments. It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other.
Example 1, the method for obtaining the aerodynamic load of the continuous wind tunnel based on the balance zero point online monitoring according to the present embodiment will be described with reference to fig. 1-2, and the method comprises the following steps:
s1, in a wind tunnel balance calibration stage, generating a wind tunnel balance calibration formula which takes response output of the wind tunnel balance as a dependent variable and a wind tunnel balance working formula which takes load as a dependent variable, wherein the method specifically comprises the following steps of:
s11, applying accurate six-dimensional force calibration load to the wind tunnel balance on the balance calibration device according to a known coordinate system and a compiled calibration load meter, and collecting response output of each component of the corresponding wind tunnel balance;
s12, fitting to generate a wind tunnel balance calibration formula taking wind tunnel balance response output as a dependent variable by applying a regression algorithm of a least square method principle; the calibration formula of each component of the wind tunnel balance with response output as a dependent variable is as follows:
；
wherein n is the component number of the wind tunnel balance, and i, j and K are indexes of components of the wind tunnel balance; r is R i The response output of the ith component of the wind tunnel balance is generated by fitting;is the zero-load output of the i-th component;Is the first order coefficient of the j-th component load to the i-th component;Is the second order square coefficient and cross term coefficient of the j and k components to the i component; p (P) j And P k Is the load of the j and k th components of the wind tunnel balance;
s13, combining the calibration formulas of all the components obtained in the S12 to generate a calibration formula of the wind tunnel balance:
；
obtaining a wind tunnel balance working formula taking load as a dependent variable of the wind tunnel balance through matrix conversion calculation:
；
where m is the number of coefficient terms for balance calibration,is composed of wind tunnel balance components>Minus->Column vectors composed later,/->Is composed of wind tunnel balance components>Matrix of coefficient terms->Is formed by the load value of each component of the wind tunnel balance>Column vectors of composition>Is composed of wind tunnel balance components>Matrix of coefficient terms>Is calculated from the load values of the components of the wind tunnel balance>And->Column vectors of composition>Is a matrix->Inverse matrix of>Is a matrix->And matrix->A matrix obtained by multiplication;
s2, in a wind tunnel test stage, collecting response output and time point data of a wind tunnel balance under at least two monitoring test working conditions; before the wind tunnel test is finished, collecting response output and time point data of the wind tunnel balance under the last monitoring test working condition, and after the wind tunnel test is finished, collecting zero points of the wind tunnel balance under the windless working condition;
s21, wind tunnel test preparation: the wind tunnel balance is arranged on the wind tunnel support, the aircraft model is arranged on the wind tunnel balance, the initial zero point of the wind tunnel balance is collected, and the test parameter for monitoring the test working condition and the assessment threshold value for the aerodynamic load out of tolerance are set;
s22, wind tunnel test blowing: starting a continuous wind tunnel, driving the wind tunnel to run to reach test parameters for monitoring test conditions, preheating for 20 minutes, and collecting wind tunnel balance response output and time point data of a first monitoring test condition;
s23, iteratively solving aerodynamic load of a first monitoring test working condition based on the initial zero point of the wind tunnel balance acquired in the S21, the response output of the wind tunnel balance acquired in the S22 and a wind tunnel balance working formula which is generated in the S1 and takes the load as a dependent variable;
s24, operating the wind tunnel according to a preset blowing test sequence working condition, collecting response output and time point data of the wind tunnel balance under each test working condition, driving the wind tunnel to operate to reach test parameters of a monitoring test working condition after the wind tunnel is operated for 30 minutes, and collecting response output and time point data of the wind tunnel balance of the monitoring test working condition;
s25, judging whether all blowing tests are finished, if yes, executing S29, otherwise, executing S26;
s26, iteratively calculating aerodynamic load of a monitoring test working condition based on the initial zero point of the wind tunnel balance acquired in S21, the response output of the wind tunnel balance acquired in S24 and a wind tunnel balance working formula which is generated in S1 and takes load as a dependent variable;
s27, carrying out difference between the aerodynamic load calculated in the step S26 and the aerodynamic load of the previous monitoring test working condition, and jumping to the step S29 when the difference is larger than an assessment threshold value set in the step S21 and the aerodynamic load exceeds the difference;
s28, repeating the steps S24-S27 until the preset blowing test sequence working conditions are all completed, driving the wind tunnel to run to reach test parameters of the monitoring test working conditions, and collecting wind tunnel balance response output and time point data of the final monitoring test working conditions;
s29, wind tunnel test is finished: and closing the wind tunnel, and collecting the zero point of the wind tunnel balance under the windless working condition.
S3, based on wind balance zero points under the windless working condition collected after wind tunnel test is finished, wind balance response output collected before wind tunnel test is finished and a wind balance working formula generated in a wind tunnel balance calibration stage, the wind balance real-time zero points under the test working condition are linearly interpolated according to time sequence, and aerodynamic load acting on an aircraft scaling model is obtained through calculation.
S31, iteratively calculating to obtain a standard aerodynamic load serving as a monitoring test working condition based on a wind tunnel balance zero point under a windless working condition, a monitoring test working condition wind tunnel balance response output acquired before a wind tunnel test is ended and a wind tunnel balance working formula;
s32, based on the standard aerodynamic load of the monitoring test working conditions and the response output of the wind tunnel balance and the wind tunnel balance calibration formula of the monitoring test working conditions collected in the test stage, resolving the real-time zero point of the wind tunnel balance under each monitoring test working condition;
s33, linearly interpolating the real-time zero point of the wind tunnel balance under the test working condition according to time sequence between the real-time zero points of the wind tunnel balance under the adjacent two monitoring test working conditions to obtain the real-time zero point of the wind tunnel balance under the preset blowing test working condition;
s34, iteratively calculating aerodynamic load of each preset blowing test working condition based on the real-time zero point of the wind tunnel balance under the preset blowing test working condition, the response output of the wind tunnel balance under the test working condition and the working formula of the wind tunnel balance.
The present embodiment further describes the present application by taking a diameter 80 rod type six-component wind tunnel balance as an example:
step one: in the wind tunnel balance calibration stage, a wind tunnel balance calibration formula which takes wind tunnel balance response output as a dependent variable and a wind tunnel balance working formula which takes load as a dependent variable are respectively generated;
the method comprises the following steps: applying accurate six-dimensional force calibration load to the wind tunnel balance on the balance calibration device according to a known coordinate system and a compiled calibration load meter, and collecting response output of each component of the corresponding wind tunnel balance;
step two: fitting to generate a wind tunnel balance calibration formula matrix taking wind tunnel balance response output as a dependent variable by applying a regression algorithm of a least square method principle, wherein the diameter 80 rod type wind tunnel balance is a six-component balance, and the wind tunnel balance calibration formula comprises 6 multiplied by 27 coefficients;
step one, three: combining the calibration formulas of all components obtained in the step two to generate a calibration formula matrix of the wind tunnel balanceFurther, a wind tunnel balance working formula matrix which takes the load as a dependent variable of the wind tunnel balance is obtained through matrix conversion calculation> Wherein->Is the column vector outputted by the response of each component of the wind tunnel balance, < >>Is a square matrix composed of first-order coefficients in a wind tunnel balance calibration formula,/for the wind tunnel balance calibration formula>Is a column vector formed by the load values of each component of the wind tunnel balance, < >>Is a matrix formed by a second-order square coefficient and a cross term coefficient in a wind tunnel balance calibration formula,is a column vector consisting of square values and cross multiplied values obtained by the calculation of the loads of the components of the wind tunnel balance,/->Is a matrix->Inverse matrix of>Is a matrix->And matrix->And multiplying the obtained matrix.
Step two: in the wind tunnel test stage, collecting response output and time point data of the wind tunnel balances under a plurality of monitoring test working conditions, and immediately collecting zero points of the wind tunnel balances under a windless working condition after the wind tunnel is shut down;
step two,: the wind tunnel test adopts a certain aircraft model, a wind tunnel balance is arranged on a wind tunnel support, and then the aircraft model is arranged on the wind tunnel balance; setting test parameters for monitoring test working conditions to be Mach number 0.75, reynolds number 300 ten thousand, attack angle 10 degrees and sideslip angle 0 degree;
step two: starting a continuous wind tunnel, driving the wind tunnel to run to reach the test parameters of the monitoring test working condition, preheating for 20 minutes, and collecting the response output of a wind tunnel balance of the first monitoring test working condition as U Y monitor 1 =2.4608，U Mz monitor 1 =-1.0468，U Mx monitor 1 =0.5331，U X monitor 1 =1.36，U Z monitoring 1 =1.796 and U My monitor 1 =1.199, set the time of acquisition to 0;
step two, three: operating the wind tunnel according to the preset blowing test sequence working conditions, and collecting wind tunnel balance responses under each test working conditionOutputting and time point data, wherein the test parameters of the test working condition are Mach number 0.9, reynolds number 300 ten thousand, attack angle 10 degrees and sideslip angle 0 degrees, and the response output of the wind tunnel balance is U Y test =3.0515，U Mz test =-1.3393，U Mx test =0.6447，U X test =1.7019，U Z test = 2.0941 and U My test = 1.4281, set the time of acquisition to 10; the wind tunnel is operated for 30 minutes, the wind tunnel is driven to operate to monitor test parameters of test working conditions, and the response output of a wind tunnel balance for monitoring the test working conditions is collected to be U Y monitor 2 =2.4618，U Mz supervision 2 =-1.0458，U Mx monitor 2 =0.5321，U X monitor 2 =1.3614，U Z monitoring 2 = 1.7948 and U My monitor 2 = 1.1979, set the time of acquisition to 30;
step two, four: closing the wind tunnel, and immediately collecting that the wind stopping zero point of the wind tunnel balance is U Y stop =0.099，U Mz stop =0.1269，U Mx stop =0.0862，U X stop =-0.1133，U Z stop = 0.631 and U My stop =0.2468。
Step three: and (3) taking the aerodynamic load of the last monitoring test working condition as a standard load, resolving the real-time zero point of the wind tunnel balance under each monitoring test working condition, and then linearly interpolating the real-time zero point of the wind tunnel balance under the test working condition according to time sequence between every two adjacent real-time zero points of the wind tunnel balance under the monitoring test working conditions, so as to obtain the aerodynamic load acting on the aircraft scaling model.
Step three: applying wind stopping zero point of wind tunnel balance and response output of wind tunnel balance and wind tunnel balance working formula matrix using load as dependent variable, and obtaining standard aerodynamic load as monitoring test working condition as Y by iterative calculation Label (C) =2124.6，Mz Label (C) =-122.4，Mx Label (C) =81.94，X Label (C) =154.81，Z Label (C) =261.8 and My Label (C) =24.41；
Step three, two: the standard aerodynamic load of the monitoring test working condition and the acquired wind tunnel balance response output under the monitoring test working condition are obtained through calculation, and the wind tunnel balance calibration formula matrix taking the wind tunnel balance response output as a dependent variable is used for calculating the wind tunnel balance real under the monitoring test working conditionThe zero point is U Y monitor 0 =0.098，U Mz monitor 0 =0.1259，U Mx monitor 0 =0.0872，U X monitor 0 =-0.1147，U Z monitoring 0 = 0.6322 and U My monitor 0 =0.2479；
And step three: applying the acquired test working condition and time point data under the test working condition to the real-time zero point of the wind tunnel balance under the time sequence linear interpolation test working condition between the real-time zero point of the wind tunnel balance under the resolved monitoring test working condition and the acquired wind stopping zero point of the wind tunnel balance, wherein the real-time zero point of the wind tunnel balance under the time sequence linear interpolation test working condition is U Y test 0 =0.0983，U Mz test 0 =0.1262，U Mx test 0 =0.0869，U X test 0 =-0.1142，U Z test 0 = 0.6318 and U My test 0 =0.2475；
And step three, four: wind tunnel balance real-time zero point under blowing test working condition obtained by interpolation and wind tunnel balance response output under corresponding test working condition obtained by acquisition, and wind tunnel balance working formula matrix taking load as dependent variable, and iteratively calculating aerodynamic load Y under each preset blowing test working condition Test =2655.74，Mz Test =-153.02，Mx Test =102.74，X Test =193.04，Z Test = 327.49 and My Test =30.39。
In embodiment 2, the computer device of the present application may be a device including a processor and a memory, for example, a single chip microcomputer including a central processing unit. And the processor is used for realizing the steps of the method for acquiring the aerodynamic load of the continuous wind tunnel based on the balance zero point on-line monitoring when executing the computer program stored in the memory.
The processor may be a central processing unit (Central Processing Unit, CPU), other general purpose processors, digital signal processors (Digital Signal Processor, DSP), application specific integrated circuits (Application Specific Integrated Circuit, ASIC), off-the-shelf programmable gate arrays (Field-Programmable Gate Array, FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or the like. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like.
The memory may mainly include a storage program area and a storage data area, wherein the storage program area may store an operating system, an application program (such as a sound playing function, an image playing function, etc.) required for at least one function, and the like; the storage data area may store data (such as audio data, phonebook, etc.) created according to the use of the handset, 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 (Flash Card), at least one disk storage device, flash memory device, or other volatile solid-state storage device.
Embodiment 3, computer-readable storage Medium embodiment
The computer readable storage medium of the present application may be any form of storage medium that is readable by a processor of a computer device, including but not limited to non-volatile memory, ferroelectric memory, etc., on which a computer program is stored, and when the processor of the computer device reads and executes the computer program stored in the memory, the steps of the method for acquiring continuous wind tunnel aerodynamic load based on balance zero on-line monitoring described above may be implemented.
The computer program comprises computer program code which may be in source code form, object code form, executable file or in some intermediate form, etc. The computer readable medium may include: any entity or device capable of carrying the computer program code, a recording medium, a U disk, a removable hard disk, a magnetic disk, an optical disk, a computer Memory, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), an electrical carrier signal, a telecommunications signal, a software distribution medium, and so forth. It should be noted that the computer readable medium contains content that can be appropriately scaled according to the requirements of jurisdictions in which such content is subject to legislation and patent practice, such as in certain jurisdictions in which such content is subject to legislation and patent practice, the computer readable medium does not include electrical carrier signals and telecommunication signals.
While the application has been described with respect to a limited number of embodiments, those skilled in the art, having benefit of the above description, will appreciate that other embodiments are contemplated within the scope of the application as described herein. Furthermore, it should be noted that the language used in the specification has been principally selected for readability and instructional purposes, and may not have been selected to delineate or circumscribe the inventive subject matter. Accordingly, many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the appended claims. The disclosure of the present application is intended to be illustrative, but not limiting, of the scope of the application, which is defined by the appended claims.
Claims (5)
1. The method for acquiring the aerodynamic load of the continuous wind tunnel based on the balance zero point on-line monitoring is characterized by comprising the following steps of:
s1, in a wind tunnel balance calibration stage, generating a wind tunnel balance calibration formula which takes response output of the wind tunnel balance as a dependent variable and a wind tunnel balance working formula which takes load as a dependent variable, wherein the method specifically comprises the following steps of:
s11, applying accurate six-dimensional force calibration load to the wind tunnel balance on the balance calibration device according to a known coordinate system and a compiled calibration load meter, and collecting response output of each component of the corresponding wind tunnel balance;
s12, fitting to generate a wind tunnel balance calibration formula taking wind tunnel balance response output as a dependent variable by applying a regression algorithm of a least square method principle; the calibration formula of each component of the wind tunnel balance with response output as a dependent variable is as follows:
；
wherein n is the component number of the wind tunnel balance, and i, j and K are indexes of components of the wind tunnel balance; r is R i The response output of the ith component of the wind tunnel balance is generated by fitting;is the zero-load output of the i-th component;Is the first order coefficient of the j-th component load to the i-th component;Is the second order square coefficient and cross term coefficient of the j and k components to the i component; p (P) j And P k Is the load of the j and k th components of the wind tunnel balance;
s13, combining the calibration formulas of all the components obtained in the S12 to generate a calibration formula of the wind tunnel balance:
；
obtaining a wind tunnel balance working formula taking load as a dependent variable of the wind tunnel balance through matrix conversion calculation:
；
where m is the number of coefficient terms for balance calibration,is composed of wind tunnel balance components>Minus->Column vectors composed later,/->Is composed of wind tunnel balance components>Matrix of coefficient terms->Is formed by the load value of each component of the wind tunnel balance>Column vectors of composition>Is composed of wind tunnel balance components>Matrix of coefficient terms>Is calculated from the load values of the components of the wind tunnel balance>And->Column vectors of composition>Is a matrix->Inverse matrix of>Is a matrix->And matrix->A matrix obtained by multiplication;
s2, in a wind tunnel test stage, collecting response output and time point data of a wind tunnel balance under at least two monitoring test working conditions; before the wind tunnel test is finished, collecting response output and time point data of a wind tunnel balance under the last monitoring test working condition; after the wind tunnel test is finished, collecting a wind tunnel balance zero point under a windless working condition;
s3, based on wind balance zero points under the windless working condition collected after wind tunnel test is finished, wind balance response output collected before wind tunnel test is finished and a wind balance working formula generated in a wind tunnel balance calibration stage, the wind balance real-time zero points under the test working condition are linearly interpolated according to time sequence, and aerodynamic load acting on an aircraft scaling model is obtained through calculation.
2. The method for acquiring the aerodynamic load of the continuous wind tunnel based on the balance zero point on-line monitoring according to claim 1, wherein the step S2 specifically comprises the following steps:
s21, wind tunnel test preparation: the wind tunnel balance is arranged on the wind tunnel support, the aircraft model is arranged on the wind tunnel balance, the initial zero point of the wind tunnel balance is collected, and the test parameter for monitoring the test working condition and the assessment threshold value for the aerodynamic load out of tolerance are set;
s22, wind tunnel test blowing: starting a continuous wind tunnel, driving the wind tunnel to run to reach test parameters for monitoring test conditions, preheating for 20 minutes, and collecting wind tunnel balance response output and time point data of a first monitoring test condition;
s23, iteratively solving aerodynamic load of a first monitoring test working condition based on the initial zero point of the wind tunnel balance acquired in the S21, the response output of the wind tunnel balance acquired in the S22 and a wind tunnel balance working formula which is generated in the S1 and takes the load as a dependent variable;
s24, operating the wind tunnel according to a preset blowing test sequence working condition, collecting response output and time point data of the wind tunnel balance under each test working condition, driving the wind tunnel to operate to reach test parameters of a monitoring test working condition after the wind tunnel is operated for 30 minutes, and collecting response output and time point data of the wind tunnel balance of the monitoring test working condition;
s25, judging whether all blowing tests are finished, if yes, executing S29, otherwise, executing S26;
s26, iteratively calculating aerodynamic load of a monitoring test working condition based on the initial zero point of the wind tunnel balance acquired in S21, the response output of the wind tunnel balance acquired in S24 and a wind tunnel balance working formula which is generated in S1 and takes load as a dependent variable;
s27, carrying out difference between the aerodynamic load calculated in the step S26 and the aerodynamic load of the previous monitoring test working condition, and jumping to the step S29 when the difference is larger than an assessment threshold value set in the step S21 and the aerodynamic load exceeds the difference;
s28, repeating the steps S24-S27 until the preset blowing test sequence working conditions are all completed, driving the wind tunnel to run to reach test parameters of the monitoring test working conditions, and collecting wind tunnel balance response output and time point data of the final monitoring test working conditions;
s29, wind tunnel test is finished: and closing the wind tunnel, and collecting the zero point of the wind tunnel balance under the windless working condition.
3. The method for acquiring the aerodynamic load of the continuous wind tunnel based on the balance zero point on-line monitoring according to claim 2, wherein the step S3 specifically comprises the following steps:
s31, iteratively calculating to obtain a standard aerodynamic load serving as a monitoring test working condition based on a wind tunnel balance zero point under a windless working condition, a monitoring test working condition wind tunnel balance response output acquired before a wind tunnel test is ended and a wind tunnel balance working formula;
s32, based on the standard aerodynamic load of the monitoring test working conditions and the response output of the wind tunnel balance and the wind tunnel balance calibration formula of the monitoring test working conditions collected in the test stage, resolving the real-time zero point of the wind tunnel balance under each monitoring test working condition;
s33, linearly interpolating the real-time zero point of the wind tunnel balance under the test working condition according to time sequence between the real-time zero points of the wind tunnel balance under the adjacent two monitoring test working conditions to obtain the real-time zero point of the wind tunnel balance under the preset blowing test working condition;
s34, iteratively calculating aerodynamic load of each preset blowing test working condition based on the real-time zero point of the wind tunnel balance under the preset blowing test working condition, the response output of the wind tunnel balance under the test working condition and the working formula of the wind tunnel balance.
4. An electronic device comprising a memory and a processor, the memory storing a computer program, the processor implementing the steps of the method of obtaining a continuous wind tunnel aerodynamic load based on balance zero point on-line monitoring of any one of claims 1-3 when executing the computer program.
5. A computer readable storage medium having stored thereon a computer program, which when executed by a processor implements the method of obtaining a continuous wind tunnel aerodynamic load based on balance zero on-line monitoring of any of claims 1-3.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116952524A (en) * | 2023-09-18 | 2023-10-27 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel dynamic derivative test monitoring method, electronic equipment and storage medium |
| CN117147095A (en) * | 2023-11-01 | 2023-12-01 | 中国航空工业集团公司沈阳空气动力研究所 | High-precision measuring device and method for aerodynamic force of rotor unmanned aerial vehicle |
| CN117928884A (en) * | 2024-03-22 | 2024-04-26 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed continuous wind tunnel operation method considering balance time-related data correction |
| CN117949164A (en) * | 2024-03-22 | 2024-04-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Time-related data correction method for high-speed continuous wind tunnel balance |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116952524A (en) * | 2023-09-18 | 2023-10-27 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel dynamic derivative test monitoring method, electronic equipment and storage medium |
| CN116952524B (en) * | 2023-09-18 | 2023-12-05 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel dynamic derivative test monitoring method, electronic equipment and storage medium |
| CN117147095A (en) * | 2023-11-01 | 2023-12-01 | 中国航空工业集团公司沈阳空气动力研究所 | High-precision measuring device and method for aerodynamic force of rotor unmanned aerial vehicle |
| CN117147095B (en) * | 2023-11-01 | 2024-01-23 | 中国航空工业集团公司沈阳空气动力研究所 | High-precision measuring device and method for aerodynamic force of rotor unmanned aerial vehicle |
| CN117928884A (en) * | 2024-03-22 | 2024-04-26 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed continuous wind tunnel operation method considering balance time-related data correction |
| CN117949164A (en) * | 2024-03-22 | 2024-04-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Time-related data correction method for high-speed continuous wind tunnel balance |
| CN117949164B (en) * | 2024-03-22 | 2024-05-28 | 中国空气动力研究与发展中心高速空气动力研究所 | Time-related data correction method for high-speed continuous wind tunnel balance |
| CN117928884B (en) * | 2024-03-22 | 2024-05-28 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed continuous wind tunnel operation method considering balance time-related data correction |
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