CN103868670A - Mach number control method of experimental section flow field of continuous transonic wind tunnel - Google Patents
Mach number control method of experimental section flow field of continuous transonic wind tunnel Download PDFInfo
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Abstract
The invention relates to a Mach number control method of an experimental section flow field of a continuous transonic wind tunnel. According to the given target Mach number, the rotation speed n of a compressor, the angle beta of a static blade and the position L of a choke finger, the initial states of the angle beta of the static blade and the position L of the choke finger keep unchangeable, and the rotation speed n of the compressor is adjusted to be a target value; after the rotation speed n of the compressor is in place, according to the set of a specific experiment, the angle beta of the static blade is adjusted to be a target value, and then the position L of the choke finger is adjusted to be a target value; when the rotation speed n of the compressor, the angle beta of the static blade and the position L of the choke finger are adjusted to be the target values, the Mach number, measured in real time, of the experimental section is compared with the target Mach number, and then the rotation speed of the compressor, the angle of the static blade and the position of the choke finger are adjusted according to the deviation value until the actual Mach number is close to the target Mach number. A thought is provided for controlling the Mach number of the experimental section flow field of the continuous transonic wind tunnel, and technical support is provided for ensuring smooth development of national advanced aircrafts.
Description
Technical field
The invention belongs to aerospace field, be specifically related to a kind of continous way transonic wind tunnel experimental section flow field Mach number control method.
Background technology
Continous way transonic wind tunnel is a kind of return circuit wind tunnel, and experimental section flow field is Transonic Flow, can carry out continuously a large amount of blowing experiments, and its structure as shown in Figure 1.Can carry out the type selecting experiment of aircraft by this wind-tunnel, for the design of advanced aerofoil profile type selecting and advanced aircraft provides technical support.
Continous way transonic wind tunnel has following features:
1) dynamic experiment
Wind-tunnel can continue the experiment flow field (Mach number is stable) that provides stable, can realize empirical model by certain mechanism moves continuously, be applicable to very much the dynamic perfromance of the military helicopter rotor of simulation high maneuverability, and its dynamic perfromance is one of study hotspot of current various countries aerodynamics worker concern.
2) incoming flow Mach number control accuracy is high
Domestic existing intermittent wind tunnel, owing to adopting high-pressure air source as power, set up the required experiment flow field of experimental section by abrupt release source of the gas, whole process does not continue several seconds to tens seconds not etc., has that Mach number control accuracy is low, flow field continuation and a shortcoming such as stability is not high.Continous way transonic wind tunnel can move continuously, and Mach number can be realized stepless control, therefore has the feature that experimental section flow field is stable, incoming flow Mach number control accuracy is high.
3) efficiency is high, cost is low
Domestic transonic speed productivity wind-tunnel all adopts high-pressure air pipe mode to store at present, calms the anger at every turn and only can make wind-tunnel work several seconds～tens second, then again calms the anger, therefore there is the feature that efficiency is low, cost is high.Continous way transonic wind tunnel can move (Mach number is controlled continuously) continuously, therefore has the feature that efficiency is high, cost is low.
A significant challenge of continous way transonic wind tunnel experiment is exactly how to control the Mach number in experimental section flow field, makes the Mach number can be adjustable continuously under normal pressure situation, meets requirement of experiment.Continous way transonic wind tunnel Mach number control essence is exactly on the basis that ensures wind tunnel operation safety, how to control the accurate control that wind-tunnel power source (rotating speed of motor and the static blade angle of axial compressor) and two venturi grid refer to realize experimental section flow field Mach number.The control mode of Mach number simply introduced in " research of NF-6 wind-tunnel Mach number Close-loop Control System Design " literary composition of " experimental fluid mechanics " fourth phase in 2010 by several curve maps, then being aided with process flow diagram is illustrated, finally provide the control effect of some, but do not related to the structure thought of continous way transonic wind tunnel Mach number control and the corresponding content such as system equipment and control mode.
Summary of the invention
The technical matters solving
For fear of the deficiencies in the prior art part, the present invention proposes a kind of continous way transonic wind tunnel experimental section flow field Mach number control method, realizes the Mach number control in continous way transonic wind tunnel flow field.
Technical scheme
A kind of continous way transonic wind tunnel experimental section flow field Mach number control method, is characterized in that step is as follows:
Step 1: the concrete numerical value that refers to L tri-parameters in position to set the goal Mach number and compressor rotary speed n, static blade angle β, grid;
Step 2: keep static blade angle β, grid to refer to that position L is constant in original state, regulate compressor rotary speed n to desired value;
Step 3: after compressor rotary speed n puts in place, according to the setting of specific experiment, first regulate static blade angle β, rear adjusting grid to refer to that position L is to desired value;
Step 4: be adjusted to after desired value when compressor rotary speed n, static blade angle β, grid refer to tri-parameters of position L, test section Mach numerical value will be recorded in real time and target Mach number is compared, regulate compressor rotary speed, stator blade angle and grid to refer to according to deviate, until actual Mach number approaches target Mach number.
Described compressor rotary speed n, static blade angle β and grid refer to that the goal-selling value of tri-parameters of position L obtains according to tunnel debug test experience.
Beneficial effect
A kind of continous way transonic wind tunnel experimental section flow field Mach number control method that the present invention proposes, by while control gate refer to, motor and axial compressor, measure in real time Mach number, under normal pressure situation, realize the foundation of wind tunnel experiment section Transonic Flow, for continous way transonic speed the Mach number control in high Reynola number wind tunnel flow field a kind of thinking is provided, for ensureing that carrying out smoothly of national advanced aircraft provides technical support.
Accompanying drawing explanation
Fig. 1 is continous way transonic wind tunnel structural representation;
1-compressor, 2-test chamber, 3-grid refer to, 4-anti-asthma bypass quick valve
Fig. 2 is continous way transonic wind tunnel Mach number control system principle of work schematic diagram;
Fig. 3 is continous way transonic wind tunnel Mach number control structure schematic diagram;
Fig. 4 is motor and axial compressor control subsystem structural representation;
Fig. 5 is motor speed control subsystem schematic diagram;
Fig. 6 is Mach number measurement subsystem structural representation;
Fig. 7 is that grid are accused system system architecture schematic diagram;
Fig. 8 is Mach number control backup system structural representation;
Fig. 9 is that schematic diagram is implemented in the control of continous way transonic wind tunnel Mach number;
Figure 10 is the Mach Number Distribution figure of experimental section model district core flow under different Mach number
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
The principle of work of Mach number control is: system selects high-precision pressure sensor (transmitter) to measure stagnation pressure and static pressure, utilize total, the static pressure calculating Mach number of survey, this calculated value enters computing machine closed loop and automatically controls, and finally obtains the target Mach number within the scope of precision index.In order to reduce system interference, sensor is output as large-signal.The A/D multifunctional data acquisition card of 16 always completes, static pressure collection, refers to that position changes Mach number, with advanced Intelligent Control Strategy control Mach number by computer control compressor electric motor rotating speed and stator blade angle or grid.Atmospheric pressure, wind-tunnel stagnation temperature and for dry gas bleed pressure and the humidity etc. of replacing soft air in hole also by this systematic survey.Mach number control system principle of work as shown in Figure 2.
The thinking of Mach number control as shown in Figure 3, comprises that motor and axial compressor control subsystem, Mach number measurement subsystem, grid refer to control subsystem, assistant subsystem, realize control and the operation of whole system by upper industrial computer.
Motor and axial compressor subsystem controls subsystem mainly complete the control of motor and axial compressor rotating speed and static blade angle, as shown in Figure 4.The steady rotating speed control of air compressor motor has computing machine given (digital quantity, analog input) and two kinds of modes of control stand manual setting, and its concrete principle control as shown in Figure 5.If adopt computing machine given way, motor speed instruction arrives motor after passing to direct current speeder by industrial computer by PLC system, the real-time rotate speed of motor feeds back the closed-loop control that realizes rotating speed in industrial computer by arrangements for speed regulation, motor speed is higher means that the kinetic energy providing to experimental section is larger, is convenient to the foundation of experimental section Transonic Flow.Under a certain fixed rotating speed of compressor, the variation at compressor stator blade angle can cause the marked change of Mach number.Compressor stator blade angle is adjusted and controlled, and is that Mach number regulates one of of paramount importance means.Can realize closed-loop control to the static blade angle on axial compressor by industrial computer, for changing the flow of suction port of compressor, indirectly change the velocity field of experimental section.
Mach number measurement subsystem mainly completes the measurement of experimental section Mach number, as shown in Figure 6.In wind-tunnel, total hydrostatic measuring point is connected with pressure transducer by pipeline, total temperature measurement is connected with temperature sensor, pressure and total measured value of temperature sensor offer data collecting card by electric signal, and industrial computer is adopted card information and passed through the Mach number instantaneous value that calculates experimental section by extracting number.
Grid refer to that control subsystem mainly completes the control that Shan Zhi mechanism grid refer to displacement, as shown in Figure 7.Wind tunnel experiment section flow field can refer to that the displacement of stretching out controls by grid, the displacement that grid refer to refers to that by servomotor control gate mechanism realizes, industrial computer passes to alternating-current servo controller by motion control card by movable information, drive the motion of servomotor, finally realize the control that grid refer to motion.
The obtaining of supplementary when backup system mainly completes Mach number control, as shown in Figure 8.Wind tunnel body running pressure obtain and wind-tunnel in the measurement of airflow humidity all will have influence on the enforcement of Mach number control.
As shown in Figure 9, step is as follows for the specific implementation method flow process of the Mach number control in continous way transonic wind tunnel flow field:
1) give the Mach number that sets the goal, call Mach number preset module, automatically from database, find compressor rotary speed n, static blade angle β, the grid that match with it to refer to the concrete numerical value of tri-parameters of position L by controlling software;
2) keep static blade angle β, grid to refer to that position L is constant in original state, progressively regulate compressor rotary speed n to desired value;
3) after compressor rotary speed n puts in place, according to the demand of specific experiment, first regulate static blade angle β, rear adjusting grid to refer to that position L is to desired value, and whether verification actual feedback is within error range, if actual parameter does not put in place, continues to regulate according to difference;
4) when three parameters are adjusted to after desired value, will record in real time test section Mach numerical value and target Mach number is compared, regulate compressor rotary speed, stator blade angle and grid to refer to according to deviate, until actual Mach number approaches target Mach number.
5) compressor rotary speed n, static blade angle β, grid refer to that the goal-selling value of tri-parameters of position L is calculated by algorithm and tunnel debug test experience, and do a little accommodation according to dissimilar test type.As wish realize that under normal pressure, Mach number reaches 0.6, in preset module, provide compressor rotary speed n, static blade angle β, grid refer to that the initial value of tri-parameters of position L is respectively: n=2500r/min, β=45 °, L=5mm.
Concrete implementation result
Figure 10 has provided the Mach Number Distribution situation of different Mach number drag district inner core stream, and in figure, horizontal ordinate is in model district, to put the distance from experimental section porch.As can be seen from the figure core flow Mach Number Distribution is very even, only in the time of Ma=1.05, has occurred certain fluctuation.Table 1 has provided the distribution scenario of the axial Mach number of experimental section model district core flow, Mach number root-mean-square-deviation, Mach Number Never To Be Exceeded deviation and Mach number gradient under different Mach number.In the time of Ma < 0.9, Mach number root-mean-square-deviation is less than 0.002, reaches the advanced index (GJB1179-91) of national military standard; And the Mach number root-mean-square-deviation of Ma >=0.9 o'clock is less than 0.005, has also reached the qualified index of national military standard (GJB1179-91).
Table 1: the distribution situation of the axial Mach number of experimental section model district core flow, Mach number root-mean-square-deviation, Mach Number Never To Be Exceeded deviation and Mach number gradient under different Mach number.
| Ma | M | ΔMmax | σ M | dM/dX |
| 0.2 | 0.2019 | 0.0011 | 0.0005 | -0.0003 |
| 0.3 | 0.3018 | 0.0020 | 0.0006 | -0.0002 |
| 0.4 | 0.4010 | 0.0024 | 0.0007 | 0.0004 |
| 0.5 | 0.5003 | 0.0030 | 0.0010 | 0.0004 |
| 0.6 | 0.6007 | 0.0035 | 0.0012 | 0.0007 |
| 0.7 | 0.6989 | 0.0041 | 0.0014 | 0.0007 |
| 0.75 | 0.7494 | 0.0046 | 0.0016 | 0.0013 |
| 0.8 | 0.7984 | 0.0046 | 0.0017 | 0.0011 |
| 0.85 | 0.8510 | 0.0049 | 0.0019 | 0.0013 |
| 0.9 | 0.9004 | 0.0054 | 0.0021 | 0.0013 |
| 0.95 | 0.9488 | 0.0057 | 0.0023 | 0.0011 |
| 1.0 | 0.9981 | 0.0064 | 0.0028 | 0.0009 |
| 1.05 | 1.0512 | 0.0184 | 0.0081 | -0.0047 |
Claims (2)
1. a continous way transonic wind tunnel experimental section flow field Mach number control method, is characterized in that step is as follows:
Step 1: the concrete numerical value that refers to L tri-parameters in position to set the goal Mach number and compressor rotary speed n, static blade angle β, grid;
Step 2: keep static blade angle β, grid to refer to that position L is constant in original state, regulate compressor rotary speed n to desired value;
Step 3: after compressor rotary speed n puts in place, according to the setting of specific experiment, first regulate static blade angle β, rear adjusting grid to refer to that position L is to desired value;
Step 4: be adjusted to after desired value when compressor rotary speed n, static blade angle β, grid refer to tri-parameters of position L, test section Mach numerical value will be recorded in real time and target Mach number is compared, regulate compressor rotary speed, stator blade angle and grid to refer to according to deviate, until actual Mach number approaches target Mach number.
2. continous way transonic wind tunnel experimental section flow field Mach number control method according to claim 1, is characterized in that: described compressor rotary speed n, static blade angle β and grid refer to that the goal-selling value of tri-parameters of position L obtains according to tunnel debug test experience.
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104483093A (en) * | 2014-12-15 | 2015-04-01 | 中国燃气涡轮研究院 | Variable mach number transonic rigid free jet nozzle |
| CN104729825A (en) * | 2015-04-03 | 2015-06-24 | 中国航天空气动力技术研究院 | Auxiliary jet-flow system for controlling high speed wind tunnel transonic flow field |
| CN106813890A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of pre-judging method for wind-tunnel Transonic Test cup superpressure |
| CN109115446A (en) * | 2018-08-01 | 2019-01-01 | 东北大学 | Based on transonic wind tunnel wind speed accuracy control method and system |
| CN110160792A (en) * | 2018-11-15 | 2019-08-23 | 北京机电工程研究所 | A kind of dynamical system dynamic simulation test method |
| CN110320002A (en) * | 2019-07-31 | 2019-10-11 | 中国航发沈阳发动机研究所 | A kind of device controlling channel-style component incoming flow parameter in icing tunnel |
| CN110361157A (en) * | 2019-08-26 | 2019-10-22 | 沈阳航空航天大学 | A kind of low speed reflux wind tunnel speed stability control method |
| CN111487440A (en) * | 2020-04-14 | 2020-08-04 | 大连凌海华威科技服务有限责任公司 | Calibration method of five-hole probe |
| CN114818369A (en) * | 2022-05-19 | 2022-07-29 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Method, system, device and medium for designing continuous transonic wind tunnel section |
| CN116499701A (en) * | 2023-06-26 | 2023-07-28 | 中国航空工业集团公司沈阳空气动力研究所 | Temporary impact type transonic wind tunnel Mach number control method, electronic equipment and storage medium |
| CN116519255A (en) * | 2023-03-13 | 2023-08-01 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number accurate control system and method for continuous transonic wind tunnel |
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| CN104483093A (en) * | 2014-12-15 | 2015-04-01 | 中国燃气涡轮研究院 | Variable mach number transonic rigid free jet nozzle |
| CN104729825A (en) * | 2015-04-03 | 2015-06-24 | 中国航天空气动力技术研究院 | Auxiliary jet-flow system for controlling high speed wind tunnel transonic flow field |
| CN104729825B (en) * | 2015-04-03 | 2017-06-16 | 中国航天空气动力技术研究院 | A kind of jet system for aiding in controlling high-speed wind tunnel Asia Transonic Flow |
| CN106813890A (en) * | 2016-12-19 | 2017-06-09 | 中国航天空气动力技术研究院 | A kind of pre-judging method for wind-tunnel Transonic Test cup superpressure |
| CN106813890B (en) * | 2016-12-19 | 2019-05-24 | 中国航天空气动力技术研究院 | A kind of pre-judging method for wind-tunnel Transonic Test cup superpressure |
| CN109115446A (en) * | 2018-08-01 | 2019-01-01 | 东北大学 | Based on transonic wind tunnel wind speed accuracy control method and system |
| CN109115446B (en) * | 2018-08-01 | 2020-04-28 | 东北大学 | Wind speed precision control method and system based on transonic wind tunnel |
| CN110160792A (en) * | 2018-11-15 | 2019-08-23 | 北京机电工程研究所 | A kind of dynamical system dynamic simulation test method |
| CN110320002B (en) * | 2019-07-31 | 2021-05-25 | 中国航发沈阳发动机研究所 | Device for controlling inflow parameters of channel-type member in icing wind tunnel |
| CN110320002A (en) * | 2019-07-31 | 2019-10-11 | 中国航发沈阳发动机研究所 | A kind of device controlling channel-style component incoming flow parameter in icing tunnel |
| CN110361157A (en) * | 2019-08-26 | 2019-10-22 | 沈阳航空航天大学 | A kind of low speed reflux wind tunnel speed stability control method |
| CN111487440A (en) * | 2020-04-14 | 2020-08-04 | 大连凌海华威科技服务有限责任公司 | Calibration method of five-hole probe |
| CN114818369A (en) * | 2022-05-19 | 2022-07-29 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Method, system, device and medium for designing continuous transonic wind tunnel section |
| CN116519255A (en) * | 2023-03-13 | 2023-08-01 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number accurate control system and method for continuous transonic wind tunnel |
| CN116519255B (en) * | 2023-03-13 | 2023-09-08 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number accurate control system and method for continuous transonic wind tunnel |
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Application publication date: 20140618 |