CN114185265A - Large-scale opening jet flow wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method - Google Patents

Large-scale opening jet flow wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method Download PDF

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CN114185265A
CN114185265A CN202210134989.XA CN202210134989A CN114185265A CN 114185265 A CN114185265 A CN 114185265A CN 202210134989 A CN202210134989 A CN 202210134989A CN 114185265 A CN114185265 A CN 114185265A
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wind tunnel
pressure
control
mach number
total pressure
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CN114185265B (en
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凌忠伟
刘为杰
田嘉懿
黄昊宇
李聪健
白本奇
叶成
吴琦
梁丽嫒
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High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
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High Speed Aerodynamics Research Institute of China Aerodynamics Research and Development Center
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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B11/00—Automatic controllers
    • G05B11/01—Automatic controllers electric
    • G05B11/36—Automatic controllers electric with provision for obtaining particular characteristics, e.g. proportional, integral, differential
    • G05B11/42—Automatic controllers electric with provision for obtaining particular characteristics, e.g. proportional, integral, differential for obtaining a characteristic which is both proportional and time-dependent, e.g. P.I., P.I.D.
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
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Abstract

The invention discloses a continuous variable Mach number control method for ultrasonic speed-fixed total pressure of a large-sized open jet wind tunnel. The control method adopts a total pressure feedforward-feedback composite control strategy, feedforward control is based on a pressure regulating characteristic curve cluster of a wind tunnel pressure regulating valve, compensation quantity of displacement of the pressure regulating valve required by the change of the profile of the spray pipe and the pressure of an air source is calculated according to the Mach number of the profile of the spray pipe and the pressure of the air source in real time in the operation process of the wind tunnel, and large interference caused by the change of the profile of the spray pipe and the pressure drop of the air source to the total pressure is eliminated; the feedback control adopts incremental PID control, and the displacement of the pressure regulating valve is continuously adjusted according to the real-time feedback of the total pressure, so that the total pressure closed-loop control is realized, and the random interference in the wind tunnel operation process is inhibited. The control method can effectively eliminate or inhibit the interference of the spray pipe profile and the air source pressure change on the total pressure control in the supersonic speed continuous variable Mach number test process of the large-sized open jet wind tunnel, and improves the accuracy, the rapidity and the robustness of the total pressure control.

Description

Large-scale opening jet flow wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a continuous variable Mach number control method for ultrasonic speed-fixed total pressure of a large-scale open jet wind tunnel.
Background
In the large-scale opening jet wind tunnel supersonic speed continuous variable Mach number test process, the total pressure control degree of difficulty is big in the stable section, has two external interference in control: firstly, the large fluctuation of the total pressure of the stable section caused by the change of the profile of the wind tunnel nozzle when the Mach number is continuously changed. And secondly, the air source pressure is rapidly reduced during the operation of the wind tunnel test, so that the air inlet flow of the pressure regulating valve is reduced, and the total pressure of the stable section is rapidly reduced. From a control theory point of view, both of these disturbances are ramp disturbances, the amplitude of which varies continuously with time. The traditional stable section total pressure feedback closed-loop control strategy can effectively inhibit step interference, but has poor interference rejection for the two kinds of slope interference, and the stable section total pressure control has large steady-state error. Although the classical PID control can reduce steady-state errors caused by slope interference by improving an integral coefficient, the increase of the integral coefficient is easy to assemble total pressure control oscillation and divergence, and in severe cases, safety risks can be brought to wind tunnel equipment and test models.
At present, a large-scale opening jet flow wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method for simultaneously solving two kinds of external interference is urgently needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a constant total pressure continuous variable Mach number control method under the supersonic working condition of a large-scale open jet wind tunnel.
The invention discloses a large-scale opening jet flow wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method, which comprises the following steps of:
s1, acquiring a characteristic curve cluster of a main air flow pressure regulating valve of a wind tunnel;
obtaining a characteristic curve cluster of the valve of the pressure regulating valve at a certain Mach number interval within the continuously variable Mach number range of the wind tunnel through theoretical analysis or actual operation test, wherein the curve quantity of the curve cluster meets the requirement of interpolation fitting in subsequent control calculation;
s2, preparing a wind tunnel test;
determining relevant test procedures and test parameters, wherein the test parameters comprise initial Mach number
Figure 830912DEST_PATH_IMAGE001
Final Mach number
Figure 768781DEST_PATH_IMAGE002
Target total pressure
Figure 735600DEST_PATH_IMAGE003
(ii) a Setting the profile of the wind tunnel nozzle at the initial Mach number
Figure 835143DEST_PATH_IMAGE001
A corresponding profile;
s3, pressurizing a wind tunnel;
opening the pressure regulating valve to a preset opening degree in an open loop control mode, wherein the preset opening degree is according to the initial Mach number
Figure 379257DEST_PATH_IMAGE001
Current source pressure
Figure 996183DEST_PATH_IMAGE004
And obtaining a valve characteristic curve of the initial Mach number; when the actual total pressure of the wind tunnel reaches the target total pressure
Figure 817508DEST_PATH_IMAGE003
When the pressure is 90% -98%, the pressurization of the wind tunnel is finished;
s4, collecting total pressure and gas source pressure;
in the wind tunnel test process, a wind tunnel control program continuously collects air source pressure and total pressure of a stable section; the obtained air source pressure and the total pressure of the stable section are subjected to preprocessing such as sliding average filtering, and accurate filtered air source pressure is obtained
Figure 589418DEST_PATH_IMAGE004
And total pressure in the stabilization section
Figure 496194DEST_PATH_IMAGE005
；
S5, total pressure composite control;
converting an open-loop control mode of wind tunnel pressurization into total pressure composite control, namely a composite control mode of total pressure feedforward plus feedback, calculating the target opening of a pressure regulating valve according to a total pressure composite control algorithm, and dividing the target opening into a feedforward control part and an increment PID control part;
s51, a total pressure feedforward control part;
nozzle real-time profile Mach number fed back by nozzle control system
Figure 510286DEST_PATH_IMAGE006
Predicting the Mach number of the spray pipe profile in the next control period
Figure 451697DEST_PATH_IMAGE007
(ii) a By using
Figure 893043DEST_PATH_IMAGE008
It is shown that the first two control periods,
Figure 411749DEST_PATH_IMAGE009
it is indicated that the previous control period,
Figure 104898DEST_PATH_IMAGE010
which indicates the current control period of the control unit,
Figure 252546DEST_PATH_IMAGE011
indicating the next control cycle;
Figure 5739DEST_PATH_IMAGE012
；
a plurality of test Mach numbers are stored in a wind tunnel test parameter libraryMaCorresponding valve characteristic curve cluster
Figure 746162DEST_PATH_IMAGE013
(ii) a By interpolation
Figure 243002DEST_PATH_IMAGE006
Corresponding pressure regulating characteristic curve of valve
Figure 18060DEST_PATH_IMAGE014
，
Figure 942154DEST_PATH_IMAGE007
Corresponding pressure regulating characteristic curve of valve
Figure 435452DEST_PATH_IMAGE015
；
According to the currently collected air source pressure
Figure 470404DEST_PATH_IMAGE016
Predicting the air source pressure of the next control period
Figure 601433DEST_PATH_IMAGE017
：
Figure 696428DEST_PATH_IMAGE018
；
Air supply pressure according to two consecutive control periods
Figure 411444DEST_PATH_IMAGE016
、
Figure 250087DEST_PATH_IMAGE017
And calculating the feedforward compensation quantity of the valve:
Figure 999737DEST_PATH_IMAGE019
；
s52, an incremental PID control part;
calculating valve position feedback control quantity, namely calculating valve position feedback control quantity brought by an incremental PID control part, namely calculating feedback control quantity of pressure regulating valve position
Figure 265633DEST_PATH_IMAGE020
：
Figure 467944DEST_PATH_IMAGE021
Wherein the content of the first and second substances,
Figure 844699DEST_PATH_IMAGE022
、
Figure 947391DEST_PATH_IMAGE023
、
Figure 384188DEST_PATH_IMAGE024
respectively as a proportional coefficient, an integral coefficient and a differential coefficient,
Figure 339375DEST_PATH_IMAGE022
、
Figure 519820DEST_PATH_IMAGE023
、
Figure 244063DEST_PATH_IMAGE024
the method comprises the steps of obtaining through a wind tunnel calibration test and storing in a wind tunnel test parameter database;
Figure 179658DEST_PATH_IMAGE025
，
Figure 231927DEST_PATH_IMAGE026
controlling error for total pressure;
s6, calculating the target valve position of the pressure regulating valve
Figure 842163DEST_PATH_IMAGE027
：
Figure 296278DEST_PATH_IMAGE028
；
Wherein the content of the first and second substances,
Figure 199512DEST_PATH_IMAGE029
the current valve position of the pressure regulating valve;
s7, controlling the valve position of the pressure regulating valve;
the pressure regulating valve control system regulates the valve position of the pressure regulating valve to a target valve position
Figure 473498DEST_PATH_IMAGE027
；
S8, the wind tunnel control program obtains the filtered total pressure according to the step S4
Figure 261326DEST_PATH_IMAGE005
Judging whether the wind tunnel flow field is stable or not by the time history curve, if so, continuously changing the Mach number, sending a Mach number changing instruction to the spray pipe profile control system by the wind tunnel flow field control system, and adjusting the spray pipe profile from the initial Mach number after the spray pipe profile control system receives the instruction
Figure 694581DEST_PATH_IMAGE001
To the final Mach number
Figure 644082DEST_PATH_IMAGE002
And Mach number of real-time profile
Figure 795578DEST_PATH_IMAGE006
Feeding back to a wind tunnel flow field control system; meanwhile, a wind tunnel measurement system collects test data;
s9, changing the state of the test model, and repeating the steps S3-S8 until the preset test content is completed;
s10, shutting down the vehicle through a wind tunnel; the Mach number of the molded surface of the spray pipe reaches the final Mach number
Figure 121517DEST_PATH_IMAGE002
Then, the target position of the pressure regulating valve
Figure 179253DEST_PATH_IMAGE027
And setting the pressure value to be zero, closing the pressure regulating valve by the pressure regulating valve control system, and shutting down the vehicle by the wind tunnel.
Further, the filtering method in step S4 is sliding average filtering, and total pressure of the stable segment is
Figure 299656DEST_PATH_IMAGE005
The filtering window is 10-20, and the pressure of an air source
Figure 672868DEST_PATH_IMAGE004
The filtering window is 10-30.
The large-scale opening jet flow wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method adopts a total pressure feedforward-feedback composite control strategy. The feedforward control is based on a wind tunnel pressure regulating valve pressure regulating characteristic curve cluster, and the feedforward controller calculates the compensation quantity of the displacement of the pressure regulating valve in the change process of the spray pipe profile and the air source pressure according to the real-time spray pipe profile Mach number and the air source pressure so as to eliminate the large interference of the spray pipe profile change and the air source pressure reduction on the total pressure. The feedback control adopts incremental PID control, and the displacement of the pressure regulating valve is continuously regulated according to the real-time feedback of the total pressure, so that the total pressure closed-loop control is realized.
The method for controlling the constant total ultrasonic speed and the constant total pressure of the large-sized open jet flow wind tunnel by continuously changing the Mach number is an applicable and feasible technical means, and the interference of the variation of the Mach number of the gas source pressure and the Mach number of the molded surface of the spray pipe in the process of the continuously changing ultrasonic speed of the large-sized open jet flow wind tunnel on the control of the total pressure can be effectively eliminated or inhibited by adopting the total pressure feedforward-feedback composite control strategy, so that the problems of low total pressure control accuracy, long control period, narrow application range and the like in the working condition of continuously changing the Mach number by the ultrasonic speed are solved, and the accuracy, the rapidity and the robustness of the total pressure control are improved.
Drawings
FIG. 1 is a flow chart of a large-scale open jet wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method of the invention;
FIG. 2 is a schematic diagram of a large-scale open jet wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method of the present invention;
fig. 3 is a wind tunnel pressure regulating characteristic curve cluster stored in a wind tunnel database of the large-scale open jet wind tunnel ultrasonic speed constant total pressure continuous variable mach number control method.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
As shown in FIG. 1, the method for controlling the continuous Mach number of the ultrasonic speed-fixed total pressure of the large-scale open jet wind tunnel comprises the following steps:
s1, acquiring a characteristic curve cluster of a main air flow pressure regulating valve of a wind tunnel;
through actual operation tests, a pressure regulating valve characteristic curve cluster with the Mach number within the range of 1.5-3.5 and the Mach number interval of 0.1 is obtained.
S2, preparing a wind tunnel test;
determining relevant test procedures and test parameters according to current test requirements, wherein the test parameters comprise initial Mach number
Figure 802498DEST_PATH_IMAGE001
Final Mach number
Figure 85712DEST_PATH_IMAGE002
Target total pressure
Figure 501650DEST_PATH_IMAGE003
(ii) a Setting the profile of the wind tunnel nozzle at the initial Mach number
Figure 503104DEST_PATH_IMAGE001
A corresponding profile;
s3, pressurizing a wind tunnel;
opening the pressure regulating valve to a preset opening degree in an open loop control mode, wherein the preset opening degree is according to the initial Mach number
Figure 295479DEST_PATH_IMAGE001
Current source pressure
Figure 433200DEST_PATH_IMAGE004
And obtaining a valve characteristic curve of the initial Mach number; when the actual total pressure of the wind tunnel reaches the target total pressure
Figure 521504DEST_PATH_IMAGE003
When 95% of the pressure is reached, the wind tunnel is pressurized;
s4, collecting total pressure and gas source pressure;
in the wind tunnel test process, a wind tunnel control program continuously collects air source pressure and total pressure of a stable section; preprocessing such as filtering the obtained air source pressure and the total pressure sliding average value of the stable section, and the total pressure of the stable section
Figure 10254DEST_PATH_IMAGE005
Has a filter window of 15, and a gas source pressure
Figure 481686DEST_PATH_IMAGE004
The filtering window is 30; obtaining accurate filtered air source pressure
Figure 598547DEST_PATH_IMAGE004
And total pressure in the stabilization section
Figure 231654DEST_PATH_IMAGE005
；
S5, total pressure composite control;
converting the open-loop control mode into total pressure composite control, namely a total pressure feedforward-feedback composite control mode, wherein a schematic diagram of the total pressure feedforward-feedback composite control mode is shown in a figure 2; calculating the target opening degree of the pressure regulating valve according to a total pressure composite control algorithm, and dividing the target opening degree into a feedforward control part and an increment PID control part;
s51, a feedforward control part;
nozzle real-time profile Mach number fed back by nozzle control system
Figure 332334DEST_PATH_IMAGE006
Predicting the Mach number of the spray pipe profile in the next control period
Figure 341878DEST_PATH_IMAGE007
(ii) a By using
Figure 313245DEST_PATH_IMAGE008
It is shown that the first two control periods,
Figure 648411DEST_PATH_IMAGE009
it is indicated that the previous control period,
Figure 580595DEST_PATH_IMAGE010
which indicates the current control period of the control unit,
Figure 16999DEST_PATH_IMAGE011
indicating the next control cycle;
Figure 718239DEST_PATH_IMAGE012
；
the wind tunnel test parameter library is stored with a plurality of commonly used test Mach numbers as shown in FIG. 3MaCorresponding valve characteristic curve cluster
Figure 83362DEST_PATH_IMAGE030
Fig. 3 shows a pressure regulating characteristic curve at 6 mach numbers; by interpolation
Figure 502842DEST_PATH_IMAGE006
Corresponding valve characteristic curve
Figure 244401DEST_PATH_IMAGE031
，
Figure 65727DEST_PATH_IMAGE007
Corresponding valve characteristic curve
Figure 601750DEST_PATH_IMAGE032
；
According to the currently collected air source pressure
Figure 508527DEST_PATH_IMAGE016
Predicting the air source pressure of the next control period
Figure 289663DEST_PATH_IMAGE017
：
Figure 231074DEST_PATH_IMAGE018
；
Air supply pressure according to two consecutive control periods
Figure 657375DEST_PATH_IMAGE016
、
Figure 176081DEST_PATH_IMAGE017
And calculating the feedforward compensation quantity of the valve:
Figure 134809DEST_PATH_IMAGE019
；
s52, an incremental PID control part;
calculating valve position feedback control quantity, namely calculating valve position feedback control quantity brought by an incremental PID control part, namely calculating feedback control quantity of pressure regulating valve position
Figure 993044DEST_PATH_IMAGE020
：
Figure 103826DEST_PATH_IMAGE033
Figure 985195DEST_PATH_IMAGE034
；
Wherein the content of the first and second substances,
Figure 606669DEST_PATH_IMAGE022
、
Figure 257093DEST_PATH_IMAGE023
、
Figure 305820DEST_PATH_IMAGE024
respectively as a proportional coefficient, an integral coefficient and a differential coefficient,
Figure 674485DEST_PATH_IMAGE022
、
Figure 834071DEST_PATH_IMAGE023
、
Figure 604581DEST_PATH_IMAGE024
the method comprises the steps of obtaining through a wind tunnel calibration test and storing in a wind tunnel test parameter database;
Figure 325674DEST_PATH_IMAGE025
，
Figure 916056DEST_PATH_IMAGE026
controlling error for total pressure;
s6, calculating the target valve position of the pressure regulating valve
Figure 20278DEST_PATH_IMAGE027
：
Figure 769928DEST_PATH_IMAGE028
；
Wherein the content of the first and second substances,
Figure 35824DEST_PATH_IMAGE029
the current valve position of the pressure regulating valve;
s7, controlling the valve position of the pressure regulating valve;
the pressure regulating valve control system regulates the valve position of the pressure regulating valve to a target valve position
Figure 238135DEST_PATH_IMAGE027
；
S8, the wind tunnel control program obtains the filtered total pressure according to the step S4
Figure 614890DEST_PATH_IMAGE005
Judging whether the wind tunnel flow field is stable or not by the time history curve, and if the wind tunnel flow field is stable, continuously changing the Mach number and the windThe hole flow field control system sends a Mach number variable instruction to the spray pipe profile control system, and the spray pipe profile control system adjusts the spray pipe profile from the initial Mach number after receiving the instruction
Figure 219047DEST_PATH_IMAGE001
To the final Mach number
Figure 921424DEST_PATH_IMAGE002
And Mach number of real-time profile
Figure 115425DEST_PATH_IMAGE006
Feeding back to a wind tunnel flow field control system; meanwhile, a wind tunnel measurement system collects test data;
s9, changing the state of the test model, and repeating the steps S3-S8 until the preset test content is completed;
s10, shutting down the vehicle through a wind tunnel; the Mach number of the molded surface of the spray pipe reaches the final Mach number
Figure 92609DEST_PATH_IMAGE002
Then, the target position of the pressure regulating valve
Figure 551272DEST_PATH_IMAGE027
And setting the pressure value to be zero, closing the pressure regulating valve by the pressure regulating valve control system, and shutting down the vehicle by the wind tunnel.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.

Claims (4)

1. The method for controlling the continuous Mach number of the ultrasonic speed-fixed total pressure of the large-sized open jet wind tunnel is characterized by comprising the following steps of:
s1, acquiring a characteristic curve cluster of a main air flow pressure regulating valve of a wind tunnel;
obtaining a valve characteristic curve cluster of the pressure regulating valve with a certain Mach number interval in the wind tunnel continuous variable Mach number range through theoretical analysis or actual operation test;
s2, preparing a wind tunnel test;
determining relevant test procedures and test parameters, wherein the test parameters comprise initial Mach number
Figure 261146DEST_PATH_IMAGE001
Final Mach number
Figure 246420DEST_PATH_IMAGE002
Target total pressure
Figure 415233DEST_PATH_IMAGE003
(ii) a Setting the profile of the wind tunnel nozzle at the initial Mach number
Figure 220378DEST_PATH_IMAGE001
A corresponding profile;
s3, pressurizing a wind tunnel;
opening the pressure regulating valve to a preset opening degree in an open loop control mode, wherein the preset opening degree is according to the initial Mach number
Figure 273784DEST_PATH_IMAGE001
Current source pressure
Figure 847985DEST_PATH_IMAGE004
And obtaining a valve characteristic curve of the initial Mach number; when the actual total pressure of the wind tunnel reaches the target total pressure
Figure 63066DEST_PATH_IMAGE003
When the pressure is 90% -98%, the pressurization of the wind tunnel is finished;
s4, collecting total pressure and gas source pressure;
in the wind tunnel test process, a wind tunnel control program continuously collects air source pressure and total pressure of a stable section; the obtained air source pressure and the total pressure of the stable section are subjected to sliding average filtering to obtain accurate filtered air source pressure
Figure 355507DEST_PATH_IMAGE004
And total pressure in the stabilization section
Figure 822392DEST_PATH_IMAGE005
；
S5, total pressure composite control;
converting an open-loop control mode of wind tunnel pressurization into total pressure composite control, namely a composite control mode of total pressure feedforward plus feedback, calculating the target opening of a pressure regulating valve according to a total pressure composite control algorithm, and dividing the target opening into a feedforward control part and an increment PID control part;
s6, calculating the target valve position of the pressure regulating valve
Figure 251099DEST_PATH_IMAGE006
：
Figure 902660DEST_PATH_IMAGE007
；
Wherein the content of the first and second substances,
Figure 682397DEST_PATH_IMAGE008
the current valve position of the pressure regulating valve;
s7, controlling the valve position of the pressure regulating valve;
the pressure regulating valve control system regulates the valve position of the pressure regulating valve to a target valve position
Figure 812027DEST_PATH_IMAGE006
；
S8, the wind tunnel control program obtains the filtered total pressure according to the step S4
Figure 360820DEST_PATH_IMAGE005
Judging whether the wind tunnel flow field is stable or not by the time history curve, if so, continuously changing the Mach number, sending a Mach number changing instruction to the spray pipe profile control system by the wind tunnel flow field control system, and adjusting the spray pipe profile from the initial Mach number after the spray pipe profile control system receives the instruction
Figure 307917DEST_PATH_IMAGE001
To the final Mach number
Figure 309371DEST_PATH_IMAGE002
And Mach number of real-time profile
Figure 508271DEST_PATH_IMAGE009
Feeding back to a wind tunnel flow field control system; meanwhile, a wind tunnel measurement system collects test data;
s9, changing the state of the test model, and repeating the steps S3-S8 until the preset test content is completed;
s10, shutting down the vehicle through a wind tunnel; the Mach number of the molded surface of the spray pipe reaches the final Mach number
Figure 645991DEST_PATH_IMAGE002
Then, the target position of the pressure regulating valve
Figure 904934DEST_PATH_IMAGE006
And setting the pressure value to be zero, closing the pressure regulating valve by the pressure regulating valve control system, and shutting down the vehicle by the wind tunnel.
2. The large-scale open jet wind tunnel ultrasonic speed constant total pressure continuous variable Mach number control method according to claim 1, characterized in that the filtering mode in the step S4 is sliding average value filtering, and total pressure of a stable section is
Figure 393684DEST_PATH_IMAGE005
The filtering window is 10-20, and the pressure of an air source
Figure 250737DEST_PATH_IMAGE004
The filtering window is 10-30.
3. The large-scale open jet wind tunnel ultrasonic speed constant total pressure continuous variable mach number control method according to claim 1, wherein the feedforward control part in the step S5 comprises the following calculation steps:
s51, according to the Mach number of the real-time molded surface of the spray pipe fed back by the spray pipe control system
Figure 774122DEST_PATH_IMAGE009
Predicting the Mach number of the spray pipe profile in the next control period
Figure 938387DEST_PATH_IMAGE010
；
Figure 648854DEST_PATH_IMAGE011
；
In the formula (I), the compound is shown in the specification,
Figure 189557DEST_PATH_IMAGE012
it is shown that the first two control periods,
Figure 567449DEST_PATH_IMAGE013
it is indicated that the previous control period,
Figure 761670DEST_PATH_IMAGE014
which indicates the current control period of the control unit,
Figure 490591DEST_PATH_IMAGE015
indicating the next control cycle;
s52, a plurality of test Mach numbers are stored in a wind tunnel test parameter libraryMaCorresponding valve characteristic curve cluster
Figure 303827DEST_PATH_IMAGE016
(ii) a By interpolation
Figure 536225DEST_PATH_IMAGE009
Corresponding pressure regulating characteristic curve of valve
Figure 42292DEST_PATH_IMAGE017
，
Figure 992931DEST_PATH_IMAGE010
Corresponding valve pressure regulating characteristicCurve
Figure 485223DEST_PATH_IMAGE018
；
According to the currently collected air source pressure
Figure 837707DEST_PATH_IMAGE019
Predicting the air source pressure of the next control period
Figure 514676DEST_PATH_IMAGE020
：
Figure 687032DEST_PATH_IMAGE021
；
S53, according to the air source pressure of two continuous control periods
Figure 107649DEST_PATH_IMAGE019
、
Figure 314639DEST_PATH_IMAGE020
And calculating the feedforward compensation quantity of the valve:
Figure 21564DEST_PATH_IMAGE022
。
4. the method for controlling the continuous Mach number of the constant total pressure of the large-scale open jet wind tunnel ultrasonic velocity according to claim 1, wherein the incremental PID control part in the step S5 needs to calculate the valve position feedback control quantity, that is, the valve position feedback control quantity brought by the incremental PID control part, that is, the feedback control quantity of the pressure regulating valve position
Figure 681215DEST_PATH_IMAGE023
：
Figure 905523DEST_PATH_IMAGE024
Figure 967020DEST_PATH_IMAGE025
；
Wherein the content of the first and second substances,
Figure 251371DEST_PATH_IMAGE026
、
Figure 398319DEST_PATH_IMAGE027
、
Figure 269060DEST_PATH_IMAGE028
respectively as a proportional coefficient, an integral coefficient and a differential coefficient,
Figure 450643DEST_PATH_IMAGE026
、
Figure 640316DEST_PATH_IMAGE027
、
Figure 274560DEST_PATH_IMAGE028
the method comprises the steps of obtaining through a wind tunnel calibration test and storing in a wind tunnel test parameter database;
Figure 840670DEST_PATH_IMAGE029
，
Figure 611180DEST_PATH_IMAGE030
the error is controlled for the total pressure.
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CN114608785A (en) * 2022-05-10 2022-06-10 中国空气动力研究与发展中心高速空气动力研究所 Method for obtaining static pressure matching accuracy of uniform area of large-range supersonic jet flow field
CN114878133A (en) * 2022-05-18 2022-08-09 西北工业大学 Variable Mach number test method in supersonic free jet
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CN114608785A (en) * 2022-05-10 2022-06-10 中国空气动力研究与发展中心高速空气动力研究所 Method for obtaining static pressure matching accuracy of uniform area of large-range supersonic jet flow field
CN114608785B (en) * 2022-05-10 2022-07-15 中国空气动力研究与发展中心高速空气动力研究所 Method for obtaining static pressure matching accuracy of uniform area of large-range supersonic jet flow field
CN114878133A (en) * 2022-05-18 2022-08-09 西北工业大学 Variable Mach number test method in supersonic free jet
CN114894427A (en) * 2022-07-14 2022-08-12 中国航空工业集团公司沈阳空气动力研究所 Control method for continuously variable Mach number
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CN114943187A (en) * 2022-07-21 2022-08-26 中国空气动力研究与发展中心高速空气动力研究所 Valve characteristic curved surface construction method based on neural network
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CN115290285A (en) * 2022-09-28 2022-11-04 中国航空工业集团公司沈阳空气动力研究所 Hypersonic wind tunnel variable target value flow field control system and method
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CN116086762B (en) * 2023-03-06 2023-06-09 中国空气动力研究与发展中心高速空气动力研究所 Three-sound-velocity free jet test device for continuously changing Mach number in supersonic test
CN116108706A (en) * 2023-04-14 2023-05-12 中国航空工业集团公司沈阳空气动力研究所 Wind tunnel circumferential seam type pressure regulating valve preset opening degree estimation method
CN116382178A (en) * 2023-06-05 2023-07-04 中国空气动力研究与发展中心高速空气动力研究所 Full-hydraulic servo driving control method for profile of jet pipe of large high-speed wind tunnel
CN116382178B (en) * 2023-06-05 2023-08-08 中国空气动力研究与发展中心高速空气动力研究所 Full-hydraulic servo driving control method for profile of jet pipe of large high-speed wind tunnel
CN116499700A (en) * 2023-06-26 2023-07-28 中国空气动力研究与发展中心高速空气动力研究所 Wind tunnel main injection pressure sectional control method and system
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