CN108693897A - The closed loop reflux of injection driving temporarily rushes formula Asia transonic wind tunnel flow field control method - Google Patents
The closed loop reflux of injection driving temporarily rushes formula Asia transonic wind tunnel flow field control method Download PDFInfo
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- CN108693897A CN108693897A CN201810538663.7A CN201810538663A CN108693897A CN 108693897 A CN108693897 A CN 108693897A CN 201810538663 A CN201810538663 A CN 201810538663A CN 108693897 A CN108693897 A CN 108693897A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D16/00—Control of fluid pressure
- G05D16/20—Control of fluid pressure characterised by the use of electric means
- G05D16/2006—Control of fluid pressure characterised by the use of electric means with direct action of electric energy on controlling means
- G05D16/2013—Control of fluid pressure characterised by the use of electric means with direct action of electric energy on controlling means using throttling means as controlling means
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Abstract
Temporarily formula Asia transonic wind tunnel flow field control method is rushed the invention discloses a kind of closed loop reflux of injection driving, it is used as the main driving of Flow Field in Wind Tunnel by the injector after diffuser, under the cooperation that return valve, additional-air inlet pressure regulator valve, exhaust shutter, grid refer to, stable Asia, Transonic Flow are established.It realizes that stable section stagnation pressure accurately controls wherein under injector pressure regulator valve and additional-air inlet pressure regulator valve collective effect, on this basis, accurately controlling for any given M numbers under the sub- transonic speed same stagnation pressure of range can be achieved under the cooperation that grid refer to system.Traditional bottom blowing type intermittent wind tunnel is upgraded to suction-type intermittent wind tunnel by the present invention, advantageously reduce the influence of incoming higher pressure gas and noise to wind-tunnel Dynamic Flow Field index, be conducive to improve Flow Field in Wind Tunnel dynamic quality, be conducive to improve the dynamic tests qualities of data such as fluctuation pressure, flutter, dynamic derivative.
Description
Technical field
It is the present invention relates to temporarily formula Asia transonic wind tunnel flow field control field is rushed, more particularly to a kind of to be directed to mating injector system
The flow field control method of formula Asia transonic wind tunnel is temporarily rushed in half reflux of system and exhaust throttle system.
Background technology
Wind-tunnel is that energy is artificially generated and control air-flow is with the flowing of simulated flight device or object ambient gas, and can measure gas
It flows the effect to object and observes a kind of pipe-like ground experiment analog machine of physical phenomenon.Not according to analog rate
Together, wind-tunnel is divided into low-speed wind tunnel (M≤0.4), high-speed wind tunnel (0.4<M≤4.5) and hypersonic wind tunnel (M >=5.0).In height
In fast wind-tunnel, it is divided into as sub- transonic wind tunnel (M=0.4~1.4) and supersonic wind tunnel (M=1.5~4.5).Wind-tunnel is to pass through
The pressure ratio of air-flow in wind-tunnel pipeline is controlled to simulate corresponding M numbers.
High velocity of sound wind-tunnel is generally wanted in order to ensure the gas flowed through in wind-tunnel pipeline can smoothly be discharged into ambient atmosphere
Static pressure outline when gas being asked to be discharged into air is higher than external environment atmospheric pressure (normally referred to as back-pressure), due to external environment air
Bucklingization is small, it is believed that and it is relative constant, it can thus be assumed that wind-tunnel back-pressure is relative constant.For wind-tunnel, different horses is simulated
Conspicuous number needs different pressure ratios, therefore, under conditions of back-pressure is constant, need different incoming stagnation pressures that could meet pressure ratio requirement.
In order to meet above-mentioned requirements, and improve Flow Field in Wind Tunnel quality, improve wind tunnel test efficiency, reduce wind tunnel operation at
Originally, realize that wind-tunnel realizes that the operation of different M numbers, the western developed countries such as USA and Europe upgrade to intermittent wind tunnel in same stagnation pressure
Continuous wind tunnel.It is different from intermittent wind tunnel, continuous wind tunnel is to provide pressure ratio by compressor, rather than change wind tunnel operation
Stagnation pressure drives the gas in wind-tunnel circuit to form stable flowing, therefore continuous wind tunnel can be built under same operation stagnation pressure
Found stable sub- Transonic Flow.And formula Asia transonic wind tunnel is temporarily rushed, other than using pressure operation mode, do not have also above-mentioned
Test capability.But the shortcomings that pressure operation mode is the close fit for needing wind-tunnel diffuser and grid to refer to system, while can also be bright
The aobvious energy consumption for increasing wind-tunnel reduces flow field quality, is unfavorable for reducing wind tunnel operation cost, can not meet low speed pressure, small
Load test test requirements document.Currently, how to realize the operation test of same stagnation pressure difference M numbers in temporarily rushing formula Asia transonic wind tunnel
Ability all lacks successful story for using for reference both at home and abroad.
Invention content
It is an object of the invention to:Temporarily rushing formula Asia transonic wind tunnel and cannot be realized under same stagnation pressure for closed loop reflux
The operation problem of different M numbers, provide a kind of closed loop reflux of injection driving temporarily rushes formula Asia transonic wind tunnel flow field control method.
The hypervelocity subsonic airflow that this method is ejected by the injector after diffuser is used as main driving, in return valve, exhaust section
Under the collective effect for flowing valve, the steady flow of air-flow in wind-tunnel circuit is realized, and realize that wind-tunnel is steady by additional-air inlet pressure regulator valve
Determine accurately controlling for section stagnation pressure, accurate adjust for referring to system by the grid after test section realizes accurately controlling for wind-tunnel M numbers, passes through
Above-mentioned control method can realize the operation test ability of different M numbers in temporarily rushing formula Asia transonic wind tunnel under same stagnation pressure.
In order to realize these purposes and other advantages according to the present invention, a kind of closed loop reflux of injection driving is provided
Formula Asia transonic wind tunnel flow field control method temporarily is rushed, is included the following steps:
Step 1: calculating output jet pipe segment type face location parameter, diffuser according to operation stagnation pressure, experiment M numbers, bleed pressure
Location parameter, injector operation stagnation pressure and corresponding position aperture, additional-air inlet stagnation pressure and corresponding position aperture, return valve position
It sets aperture, exhaust throttle valve position aperture and grid and refers to position aperture;
Step 2: according to given parameter is calculated in step 1, by control system, by jet pipe segment type face, diffusion segment type
Face, return valve, exhaust shutter, grid refer to position aperture and are preset to given target location;And open injector system and
The shut-off valve and quick valve of additional-air inlet system;
Step 3: injector pressure regulator valve is opened, the goal pressure given in closed-loop control injector pressure to step 1;
Step 4: after injector pressure reaches closed-loop control precision in step 3, additional-air inlet pressure regulator valve, closed loop are opened
The target stagnation pressure given in stable section stagnation pressure to step 1 is controlled, and using stable section stagnation pressure as closed loop feed back object, is closed
Ring controls additional-air inlet pressure regulation valve opening, realizes the closed-loop control of stable section stagnation pressure;
Step 5: on the basis of stable section stagnation pressure reaches control accuracy, it is anti-as closed-loop control using the test section numbers of M in room
Object is presented, closed-loop control grid refer to position aperture, realize the closed-loop control of the sub- Transonic Test section numbers of M in room;
Step 6: after completing blowing test by set flow, while to additional-air inlet pressure regulator valve and quick valve, injection
Pressure regulator valve and quick valve assign shutdown command, it is ensured that additional-air inlet pressure regulator valve and quick valve, injection pressure regulator valve and quick valve are closed;
Step 7: closing all shut-off valves of wind-tunnel, complete blowing test flow is completed.
Preferably, temporarily rushing formula Asia transonic wind tunnel includes:Reflux line;The 4th be connected in turn on reflux line turns
Angle section, stable section, contraction section, nozzle section, test section, brace sections, diffuser, injector system, the first round corner section, the second turning
Section, additional-air inlet system, return valve, the 5th round corner section, exhaust system and third round corner section;
Wherein, the injector system includes:Injector;The injection admission line that is connected on injector and being connected to draws
Inject the injection pressure regulator valve in feed channel;
The additional-air inlet system includes:The additional-air inlet pipeline that is connected on reflux line and it is connected to auxiliary inlet manifold
Additional-air inlet regulating valve on road;
The exhaust system includes:Discharge duct, the exhaust shutter being connected on discharge duct and exhausting silencer tower.
Preferably, it needs to debug by wind-tunnel in step 1, establishes wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure
With injector pressure and corresponding valve location, additional-air inlet stagnation pressure and corresponding valve location, return valve aperture, exhaust throttle
Valve opening, grid refer to the functional relation between the aperture of position, and specific functional relation is:
According to function
SNOZZLE=f (M), HSDT=g (M)
Calculate separately out the nozzle contour under given M numbers and ultra-expanded section type face (diffusion segment type face), SNOZZLEFor nozzle type
Face, HSDTFor ultra-expanded section type face (diffusion segment type face);Wherein,
P0 is steady=ξ × P0 is anti-
P0 is steadyFor stable section stagnation pressure, P0 is anti-For wind-tunnel back-pressure, ξ is pressure ratio coefficient, ξ be the function of Mach number wherein,
P02=(1+ ζ1+ζ2+…+ζn)P0 is steady
P in formula02Represent injector collection chamber stagnation pressure, ζnRepresent the pressure drop coefficient of n-th of section;Wherein,
S=f (ε) × Smax, ε=P02/P01
P01Air source stagnation pressure is represented, ε indicates that pressure ratio before and after pressure regulator valve, f (ε) indicate between valve location relative opening degree and pressure ratio
Functional relation, different M numbers f (ε) are different, SmaxValve maximum position aperture is represented, S represents valve physical location aperture;Its
In,
LFF=f (M, P0 is steady)
LFFIt represents grid and refers to extended length, M is Mach number, f (M, P0 is steady) be Mach number and stable section stagnation pressure function, according to
α=f (M, P0 is steady),A1=α A2
Return valve aperture is calculated, α is the relative opening degree of return valve, and α is M numbers and P0 is steadyFunction, A1,A2Point
Not Wei return valve entrance and exit area;
According to formula
Calculate the flow of test chamber, G representation quality flows in formula, ATRepresent cross-sectional area, T0Total temperature is represented, then
According to the conservation of mass, according to formula
GAdditional-air inlet=η × GTest section, η=F (M, P0 is steady)
Additional-air inlet pressure regulator valve flow is calculated, η is discharge coefficient in formula, is M numbers and P0 is steadyFunction.
According to formula
P02 is auxiliary=ξ P0 reflux is adjusted
The stagnation pressure after additional-air inlet pressure regulator valve is calculated, according to formula
Calculate q (λ) data of auxiliary pressure-regulating valve, in formula, FTPFor pipeline area after auxiliary pressure-regulating valve, according to formula
Calculate valve port velocity coeffficient λω, in formula, F is the cyclic annular circulation area of valve, according to formula
S=f (ε) × Smax, ε=P02 is auxiliary/P01
Calculate the valve location aperture of auxiliary pressure-regulating valve.
Grid, which are calculated, according to formula refers to elongation:
Lflap=f (σ, M), σ=P03/P0 is steady
In formula, LflapRefer to elongation, P for grid03For grid segment entrance section stagnation pressure.
Exhaust throttle valve opening is calculated according to formula:
In formula, αRowFor exhaust shutter relative opening degree, S is exhaust shutter circulation area, S0It is horizontal after exhaust shutter
Sectional area, GInjectorFor injector pressure regulator valve mass flow, GAdditional-air inletFor additional-air inlet pressure regulator valve mass flow, GTest sectionFor test section
Mass flow, ρ are gas density, and ν is exhaust shutter gas flow rate, is M numbers and P0 is steadyFunction.
Preferably, it is flowed into surely in step 2 by controlling gas in return valve aperture control wind-tunnel reflux line
Determine the flow of section.
Preferably, in step 2 by controlling exhaust throttle valve opening discharge duct discharge wind-tunnel time is flowed through to adjust
Gas flow in flow path is conducive to the gas stagnation pressure for improving return valve region.
Preferably, the supersonic flow that injector ejects in step 3 is total to return valve and exhaust shutter
Under same-action, air-flow is made to form steady and sustained flowing in wind-tunnel circuit.
In the present invention, the detailed process of step 1 is:Calculate controlling test parameter:According to given operation stagnation pressure, examination
M numbers and bleed pressure are tested, brings stagnation pressure, M numbers, injection stagnation pressure, additional-air inlet stagnation pressure, return valve aperture, exhaust shutter into
Aperture, jet pipe segment type face, is spread in the function in segment type face at grid finer opening, and it is total to calculate corresponding injection stagnation pressure, additional-air inlet
Pressure, return valve aperture, exhaust throttle valve opening, grid finer opening, nozzle contour and diffusion segment type face, and according to injection stagnation pressure
Stagnation pressure is brought into valve bit function with additional-air inlet stagnation pressure, calculates the position of corresponding injection pressure regulator valve and additional-air inlet pressure regulator valve
Set aperture.
In the step two of the present invention, by servo hydraulic oil cylinder (or servo motor) by return valve, exhaust throttle
Valve and grid refer to the position aperture given in system intialization to step 1.
The present invention includes at least following advantageous effect:
(1) present invention is used as driving by the injector system positioned at diffuser rear portion, establishes and stablizes in wind-tunnel circuit
Air-flow flowing, will be traditional under blow temporarily rush formula Asia transonic wind tunnel upgrade to diffuser rear portion suction temporarily rush formula Asia transonic speed wind
Hole.
(2) present invention may be implemented temporarily to rush the examination that formula Asia transonic wind tunnel establishes Asia, Transonic Flow under same stagnation pressure
Ability is tested, and traditional intermittent wind tunnel is that do not have the test capability completely.
(3) present invention can run stagnation pressure (even under conditions of ensureing that wind-tunnel pressure ratio is constant in lower stable section
Negative pressure), run under lower ram compression and smaller flow, advantageously reduce the risk of wind tunnel test safety.
(4) present invention is relative to traditional intermittent wind tunnel, under the conditions of identical air source volume, when having longer blowing
Between, lower bleed pressure requirement.
(5) present invention can realize the simulation of negative pressure, normal pressure and pressure operation operating mode in intermittent wind tunnel, effectively widen
The operation envelope curve and simulation context of wind-tunnel.And negative pressure operation is conducive to carry out the smooth development of microstrain small-range dynamometer check.
(6) present invention may be implemented to determine M numbers, become the operating condition of ram compression, be conducive to carry out the smooth of aeroelastic effect test
Carry out.
(7) traditional bottom blowing type intermittent wind tunnel is upgraded to suction-type intermittent wind tunnel by the present invention, is advantageously reduced and
The influence of high pressure draught pulsation and noise to wind-tunnel Dynamic Flow Field index is flowed, is conducive to improve Flow Field in Wind Tunnel dynamic quality, favorably
In dynamic tests qualities of data such as raising fluctuation pressure, flutter, dynamic derivatives.
Part is illustrated to embody by further advantage, target and the feature of the present invention by following, and part will also be by this
The research and practice of invention and be understood by the person skilled in the art.
Description of the drawings:
Fig. 1 is wind-tunnel aerodynamic profile schematic diagram related to the present invention;
Fig. 2 is that the temporary of the present invention rushes formula Asia transonic wind tunnel flow field control method flow diagram.
Specific implementation mode:
Present invention will be described in further detail below with reference to the accompanying drawings, to enable those skilled in the art with reference to specification text
Word can be implemented according to this.
It should be appreciated that such as " having ", "comprising" and " comprising " term used herein do not allot one or more
The presence or addition of a other elements or combinations thereof.
Fig. 1 is wind-tunnel aerodynamic profile schematic diagram related to the present invention, as shown in Figure 1, the wind-tunnel includes:Reflux line;
It is connected to the 4th round corner section 1 on reflux line in turn, stable section 2, contraction section 3, nozzle section 4, test section 5, brace sections 6, expands
Scattered section 7, injector system 8, the first round corner section 9, the second round corner section 10, additional-air inlet system 11, return valve the 12, the 5th turn
Angle section 13, exhaust system 14 and third round corner section 15;
Wherein, the injector system 8 includes:Injector 81;82 He of injection admission line being connected on injector 81
The injection pressure regulator valve 83 being connected on injection admission line 82;
The additional-air inlet system 11 includes:The additional-air inlet pipeline 111 that is connected on reflux line and it is connected to auxiliary
Additional-air inlet regulating valve 112 on admission line 111;
The exhaust system 14 includes:Discharge duct 141, the exhaust shutter 142 being connected on discharge duct 141 and row
Gas silencing tower 143.
The wind-tunnel pneumatic structure of the present invention is temporarily rushed in the transonic wind tunnel of formula Asia in conventional half reflux, is configured after diffuser
A set of injector system for having independent pressure control, configures a set of additional-air inlet system 11, second in the second round corner section 10
Return valve system 12 is configured between round corner section 10 and third round corner section 15, in the 5th round corner section 13 and exhausting silencer tower 143
Between configure a set of exhaust throttle valve system 142.
As shown in Figure 1, wind-tunnel primary air through injector admission line 82 and valve system (injection pressure regulator valve 83) into inlet air
In the pipeline of hole, supersonic speed free jet is formed by injector 81 and be used as driving, promotion air-flow priority flow through the first round corner section 9,
Reflux line I 16, the second round corner section 10 are simultaneously shunted in 12 position of return valve:A part of air-flow is through return valve
12 enter reflux line II 17, third round corner section 15, reflux line III 18, the 4th round corner section 1, stable section 2, contraction section 3, jet pipe
Section 4, test section 5, brace sections 6, diffuser 7 and injector 81 form the reflux of closed loop;Another part air-flow is not adjusted by flowing back
Section valve 12 is directly discharged into after flowing directly into the 5th round corner section 13, discharge duct 141, exhaust shutter 142 and exhausting silencer tower 143
Air.Wind-tunnel additional-air inlet is flowed directly by additional-air inlet pipeline 111, additional-air inlet pressure regulator valve 112 and return valve 12
Reflux line II 17, then again by third round corner section 15, reflux line III 18, the 4th round corner section 1, stable section 2, contraction section 3,
The supersonic speed free jet ejected with injector after nozzle section 4, test section 5, brace sections 6, diffuser 7, injector 81 is mixed
It closes, repeats above-mentioned flow path and form complete closed-loop flow, and so on form stable flowing.Wherein specific Mach number
Control method is:Output nozzle contour location parameter, diffuser are calculated according to operation stagnation pressure, experiment M numbers, bleed pressure before blowing
Location parameter, injector operation stagnation pressure and corresponding position aperture, additional-air inlet stagnation pressure and corresponding position aperture, return valve position
It sets aperture, exhaust throttle valve position aperture, grid and refers to position aperture;And preset return valve aperture, exhaust throttle valve opening and
Grid refer to position aperture, and nozzle contour and diffusion segment type face are adjusted in place, and when blowing test, open injector pressure regulator valve to giving
After aperture is set in positioning, closed-loop control injector operating pressure opens additional-air inlet tune after injector pressure reaches control accuracy
After pressure valve to given position aperture, closed-loop control stable section stagnation pressure passes through closed loop control after stable section stagnation pressure reaches control accuracy
Grid finer opening processed realizes accurately controlling for the test section numbers of M in room, then carries out set blowing test flow until experiment is tied
Beam.It using control method provided by the invention, can temporarily be rushed in the transonic wind tunnel of formula Asia in half reflux, realize that the same operation is total
Stable Asia, Transonic Flow are established in pressure, while negative pressure, normal pressure and the blowing test of supercharging can also be realized in above-mentioned wind-tunnel
Function.It breaches and traditional temporarily rush formula Asia transonic wind tunnel different Mach number and need to match the limitation requirement of different stable section stagnation pressures.
Wind-tunnel stagnation pressure, ram compression and test section flow can be substantially reduced using the invention simultaneously, advantageously reduce the security risk of wind-tunnel,
Ensure the safety of wind-tunnel and test model.
As shown in Figure 1, the effect of injection pressure regulator valve 83 is according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure and injection
The functional relation of pressure regulation valve opening determines the position aperture of the valve, is driven for controlling injection pressure and flow, and as wind-tunnel
Primary air, driving wind-tunnel loop gas flow form closed-loop flow.
As shown in Figure 1, the effect of return valve 12 is according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure and reflux
The functional relation of control valve opening determines the position aperture of the valve, and wind-tunnel time is flowed into for controlling the incoming through the second round corner section 10
The flow in flow tube road II.
As shown in Figure 1, the effect of exhaust shutter 142 is according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure and row
The functional relation of gas throttle valve opening determines the position aperture of the valve, for controlling the gas flow for flowing through exhaust shutter, with
Improve the gas pressure of wind-tunnel return valve section.
As shown in Figure 1, the effect of additional-air inlet system 11 be according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure with it is auxiliary
The functional relation of admission pressure and pressure regulation valve position aperture is helped to determine the position aperture of the pressure and the valve of additional-air inlet, for carrying
The control accuracy of high stable section stagnation pressure realizes that wind-tunnel determines the operation function of stagnation pressure.
Wherein, above-mentioned functional relation is specially:
According to function
SNOZZLE=f (M), HSDT=g (M)
Calculate separately out the nozzle contour under given M numbers and ultra-expanded section type face (diffusion segment type face), SNOZZLEFor nozzle type
Face, HSDTFor ultra-expanded section type face (diffusion segment type face);Wherein,
P0 is steady=ξ × P0 is anti-
P0 is steadyFor stable section stagnation pressure, P0 is anti-For wind-tunnel back-pressure, ξ is pressure ratio coefficient, ξ be the function of Mach number wherein,
P02=(1+ ζ1+ζ2+…+ζn)P0 is steady
P in formula02Represent injector collection chamber stagnation pressure, ζnRepresent the pressure drop coefficient of n-th of section;Wherein,
S=f (ε) × Smax, ε=P02/P01
P01Air source stagnation pressure is represented, ε indicates that pressure ratio before and after pressure regulator valve, f (ε) indicate between valve location relative opening degree and pressure ratio
Functional relation, different M numbers f (ε) are different, SmaxValve maximum position aperture is represented, S represents valve physical location aperture;Its
In,
LFF=f (M, P0 is steady)
LFFIt represents grid and refers to extended length, M is Mach number, f (M, P0 is steady) be Mach number and stable section stagnation pressure function, according to
α=f (M, P0 is steady),A1=α A2
Return valve aperture is calculated, α is the relative opening degree of return valve, and α is M numbers and P0 is steadyFunction, A1,A2Point
Not Wei return valve entrance and exit area;
According to formula
Calculate the flow of test chamber, G representation quality flows in formula, ATRepresent cross-sectional area, T0Total temperature is represented, then
According to the conservation of mass, according to formula
GAdditional-air inlet=η × GTest section, η=F (M, P0 is steady)
Additional-air inlet pressure regulator valve flow is calculated, η is discharge coefficient in formula, is M numbers and P0 is steadyFunction.
According to formula
P02 is auxiliary=ξ P0 reflux is adjusted
The stagnation pressure after additional-air inlet pressure regulator valve is calculated, according to formula
Calculate q (λ) data of auxiliary pressure-regulating valve, in formula, FTPFor pipeline area after auxiliary pressure-regulating valve, according to formula
Calculate valve port velocity coeffficient λω, in formula, F is the cyclic annular circulation area of valve, according to formula
S=f (ε) × Smax, ε=P02 is auxiliary/P01
Calculate the valve location aperture of auxiliary pressure-regulating valve.
Grid, which are calculated, according to formula refers to elongation:
Lflap=f (σ, M), σ=P03/P0 is steady
In formula, LflapRefer to elongation, P for grid03For grid segment entrance section stagnation pressure.
Exhaust throttle valve opening is calculated according to formula:
In formula, αRowFor exhaust shutter relative opening degree, SRowFor exhaust shutter circulation area, S0 rowAfter exhaust shutter
Cross-sectional area, GInjectorFor injector pressure regulator valve mass flow, GAdditional-air inletFor additional-air inlet pressure regulator valve mass flow, GTest sectionFor experiment
Section mass flow, ρ are gas density, and ν is exhaust shutter gas flow rate, is M numbers and P0 is steadyFunction.
Fig. 2 is that a kind of the temporary of closed loop reflux of injection driving of the present invention rushes formula Asia transonic wind tunnel flow field control method
Flow chart, control method include the following steps:
Step 01:Program initial actuating is controlled, into procedure preparation stage.
Step 02:Calculate test parameters.It is required according to wind-tunnel flyoff, giving wind tunnel operation stagnation pressure, (i.e. stable section is total
Pressure), experiment M numbers, model attitude angle.Stagnation pressure, experiment M numbers and bleed pressure input parameter calculation procedure will be run, will be calculated defeated
Go out nozzle contour location parameter, diffuser location parameter, injector operation stagnation pressure and corresponding position aperture, return valve position
Aperture, exhaust throttle valve position aperture, additional-air inlet stagnation pressure and corresponding position aperture, grid refer to position aperture.
Step 03:Preset position aperture, and open shut-off valve and quick valve.It is specific as follows:Control program passes through control room
Host computer remote control testing ground slave computer assigns action command, and action command and location parameter are loaded into slave computer, under
Position machine assigns action command to each control object respectively by driver:It is assigned entirely to the shut-off valve and quick valve of injector system
Open order;Breakdown action is assigned to return valve, and calculated specific bit in closed-loop control its position aperture to step 02
Set aperture;Breakdown action is assigned to exhaust shutter, and calculated specific bit in closed-loop control its position aperture to step 02
Set aperture;Standard-sized sheet order is assigned to the shut-off valve and quick valve of additional-air inlet system;Instruction is assigned to diffuser system, will be spread
Section is adjusted to sizing face;Instruction is assigned to lance system, and nozzle contour is adjusted to sizing face.
Step 04:Injection pressure regulator valve is opened to given aperture, closed-loop control injection stagnation pressure.It is specific as follows:It is logical to control program
It crosses control room host computer remote control testing ground slave computer and assigns action command, slave computer is by driver to injector pressure regulation
Valve servo-drive system assigns open command, and injector pressure regulator valve is opened in place by calculated position in step 02, then with
Injector pressure realizes injector pressure as closed loop feed back object, the position aperture of closed-loop control injector pressure regulator valve
Closed-loop control requirement.
Step 05:Judge whether injector pressure reaches control accuracy requirement.It is specific as follows:Control system is surveyed by scene
The pressure of quantity sensor acquisition is monitored the pressure change of injector, after injection pressure meets control accuracy requirement, then
Next step control command is executed, conversely, continuing waiting for, until injection pressure is transferred to next control command after meeting control accuracy.
Step 06:Additional-air inlet pressure regulator valve is opened to given aperture, closed-loop control stable section stagnation pressure.It is specific as follows:Control
Program assigns action command by control room host computer remote control testing ground slave computer, and slave computer is by driver to auxiliary
Air inlet pressure regulator valve servo-drive system assigns open command, and additional-air inlet pressure regulator valve is opened by calculated position in step 02 and is arrived
Position, then using stable section stagnation pressure as closed loop feed back object, the position aperture of closed-loop control additional-air inlet pressure regulator valve is realized
The closed-loop control requirement of stable section stagnation pressure.
Step 07:Judge whether stable section stagnation pressure reaches control accuracy requirement.It is specific as follows:Control system is surveyed by scene
The pressure of quantity sensor acquisition is monitored the variation of stable section stagnation pressure, after stable section stagnation pressure meets control accuracy requirement,
Next step control command is then executed, conversely, continuing waiting for, until stable section stagnation pressure is transferred to next control life after meeting control accuracy
It enables.
Step 08:Closed-loop control grid finer opening adjusts M numbers.It is specific as follows:It is long-range by control room host computer to control program
Control experiment scene slave computer assigns action command, and slave computer refers to servo-drive system to grid by driver and assigns instruction, with experiment
For the section numbers of M in room as closed loop feed back object, the position aperture that closed-loop control grid refer to realizes the closed loop of the test section numbers of M in room
Control requires.
Step 09:Judge whether M numbers reach control accuracy requirement.It is specific as follows:Control system is sensed by in-site measurement
Stable section stagnation pressure (the P of device acquisition0) and test section static pressure in room (PCT) variation be monitored, and according to following formula
The test section numbers of M in room are calculated, and refer to the feedback target of closed-loop control as grid with the numbers of M in room, closed-loop control examination
The section numbers of M in room are tested, after the numbers of M in room meet control accuracy requirement, then execute next step control command, conversely, continuing waiting for, directly
It is transferred to next control command after meeting control accuracy to the numbers of M in room.
Step 10:Wind tunnel test is carried out by set blowing flow.It is specific as follows:When control system meets step 01 to step
After 09 control requires, it is transferred to formal blowing flow.And be changed according to the model attitude angle given in step 02, measure depanning
Aerodynamic loading suffered by type.
Step 11:Whether judgment models blowing flow is completed.It is specific as follows:Whether judgment models attitude angle is according to step 02
In give condition be finished, if complete, downstream is transferred to, conversely, continuing to execute correlation test.
Step 12:It cut-offs.It is specific as follows:Control program passes through under the slave computer of control room host computer remote control testing ground
Up to action command, slave computer is by driver to injector system and the pressure regulator valve servo-drive system of additional-air inlet system, quick valve
Servo-drive system, shut-off valve system assign fully closed instruction, while referring to servo-drive system to grid and assigning back to zero instruction.
Step 13:Judge whether to close in place.It is specific as follows:According to ejection system and additional-air inlet system quick valve, adjust
The limit switch of pressure valve and shut-off valve judges whether valve closes in place, while the linear displacement transducer for referring to by grid system is sentenced
Disconnected grid refer to system whether back to zero in place, if all close or back to zero in place, control system stops publication and cut-offs instruction, conversely,
Continue to send instruction of cut-offfing, until closing.
Step 14:Terminate.After control system executes the step 01 to step 13, show primary complete blowing test knot
Beam.It can stop wind tunnel test or continue to prepare blowing test next time.
Although the embodiments of the present invention have been disclosed as above, but its is not only in the description and the implementation listed
With it can be fully applied to various fields suitable for the present invention, for those skilled in the art, can be easily
Realize other modification, therefore without departing from the general concept defined in the claims and the equivalent scope, the present invention is simultaneously unlimited
In specific details and legend shown and described herein.
Claims (6)
1. a kind of closed loop reflux of injection driving temporarily rushes formula Asia transonic wind tunnel flow field control method, which is characterized in that including
Following steps:
Step 1: calculating output jet pipe segment type face location parameter, diffusion fragment position according to operation stagnation pressure, experiment M numbers, bleed pressure
Parameter, injector operation stagnation pressure and corresponding position aperture, additional-air inlet stagnation pressure and corresponding position aperture, return valve position are opened
Degree, exhaust throttle valve position aperture and grid refer to position aperture;
Step 2: according to given parameter is calculated in step 1, by control system, by jet pipe segment type face, diffusion segment type face, return
Stream regulating valve, exhaust shutter, grid refer to position aperture and are preset to given target location;And open injector system and assist into
The shut-off valve and quick valve of gas system;
Step 3: injector pressure regulator valve is opened, the goal pressure given in closed-loop control injector pressure to step 1;
Step 4: after injector pressure reaches closed-loop control precision in step 3, additional-air inlet pressure regulator valve, closed-loop control are opened
The target stagnation pressure given in stable section stagnation pressure to step 1, and using stable section stagnation pressure as closed loop feed back object, closed loop control
Additional-air inlet pressure regulation valve opening processed realizes the closed-loop control of stable section stagnation pressure;
Step 5: on the basis of stable section stagnation pressure reaches control accuracy, using test section M in room numbers as closed loop feed back pair
As closed-loop control grid refer to position aperture, realize the closed-loop control of the sub- Transonic Test section numbers of M in room;
Step 6: after completing blowing test by set flow, while to additional-air inlet pressure regulator valve and quick valve, injection air inlet
Pressure regulator valve and quick valve assign shutdown command, it is ensured that additional-air inlet pressure regulator valve and quick valve injection air inlet pressure regulator valve and quick valve close
It closes;
Step 7: closing all shut-off valves of wind-tunnel, complete blowing test flow is completed.
2. the closed loop reflux of injection driving as described in claim 1 temporarily rushes formula Asia transonic wind tunnel flow field control method,
It is characterized in that, temporarily rushing formula Asia transonic wind tunnel includes:Reflux line;It is connected to the 4th round corner section on reflux line, steady in turn
Determine section, contraction section, nozzle section, test section, brace sections, diffuser, injector system, the first round corner section, the second round corner section, auxiliary
Gas handling system, return valve, the 5th round corner section, exhaust system and third round corner section;
Wherein, the injector system includes:Injector;The injection admission line that is connected on injector and be connected to injection into
Injection pressure regulator valve in feed channel;
The additional-air inlet system includes:It the additional-air inlet pipeline that is connected on reflux line and is connected on additional-air inlet pipeline
Additional-air inlet regulating valve;
The exhaust system includes:Discharge duct, the exhaust shutter being connected on discharge duct and exhausting silencer tower.
3. the closed loop reflux of injection driving as claimed in claim 2 temporarily rushes formula Asia transonic wind tunnel flow field control method,
It is characterized in that, needs to debug by wind-tunnel in step 1, establish wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure and injector
Pressure and corresponding valve location, additional-air inlet stagnation pressure and corresponding valve location, return valve aperture, exhaust throttle valve opening,
Grid refer to the functional relation between the aperture of position.
4. the closed loop reflux of injection driving as claimed in claim 2 temporarily rushes formula Asia transonic wind tunnel flow field control method,
It is characterized in that, the stream that gas in wind-tunnel reflux line flows into stable section is controlled by controlling return valve aperture in step 2
Amount.
5. the closed loop reflux of injection driving as claimed in claim 2 temporarily rushes formula Asia transonic wind tunnel flow field control method,
It is characterized in that, is flowed through in discharge duct discharge wind-tunnel reflux road by controlling exhaust throttle valve opening to adjust in step 2
Gas flow is conducive to the gas stagnation pressure for improving return valve region.
6. the closed loop reflux of injection driving as claimed in claim 2 temporarily rushes formula Asia transonic wind tunnel flow field control method,
It is characterized in that, collective effect of the supersonic flow that injector ejects in step 3 in return valve and exhaust shutter
Under, so that air-flow is formed steady and sustained flowing in wind-tunnel circuit.
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|---|---|---|---|---|
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103123504A (en) * | 2012-12-18 | 2013-05-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Speed change pressure flow field control method applicable to intermittent transonic speed wind tunnel |
| JP2015045620A (en) * | 2013-08-29 | 2015-03-12 | 株式会社大気社 | Wind tunnel test device |
| CN104833476A (en) * | 2015-06-01 | 2015-08-12 | 中国航天空气动力技术研究院 | Low Mach number system of trisonics wind tunnel |
| CN106527519A (en) * | 2016-12-07 | 2017-03-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for controlling adjusting dynamic pressure flow field for large direct-current blow-down supersonic wind tunnel |
| CN106768795A (en) * | 2016-12-21 | 2017-05-31 | 中国航天空气动力技术研究院 | It is a kind of for temporarily rushing the sub- method across sub- across the flow field injection driving of super wind-tunnel of formula |
-
2018
- 2018-05-30 CN CN201810538663.7A patent/CN108693897B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103123504A (en) * | 2012-12-18 | 2013-05-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Speed change pressure flow field control method applicable to intermittent transonic speed wind tunnel |
| JP2015045620A (en) * | 2013-08-29 | 2015-03-12 | 株式会社大気社 | Wind tunnel test device |
| CN104833476A (en) * | 2015-06-01 | 2015-08-12 | 中国航天空气动力技术研究院 | Low Mach number system of trisonics wind tunnel |
| CN106527519A (en) * | 2016-12-07 | 2017-03-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for controlling adjusting dynamic pressure flow field for large direct-current blow-down supersonic wind tunnel |
| CN106768795A (en) * | 2016-12-21 | 2017-05-31 | 中国航天空气动力技术研究院 | It is a kind of for temporarily rushing the sub- method across sub- across the flow field injection driving of super wind-tunnel of formula |
Non-Patent Citations (3)
| Title |
|---|
| ŞEMSI ÇOŞKUN，ETC: "Experimental investigation of wake flow field and wind comfort characteristics of fractal wind fences", 《JOURNAL OF WIND ENGINEERING AND INDUSTRIAL AERODYNAMICS》 * |
| 秦建华，等: "0.6米暂冲式跨超声速风洞流场控制系统设计", 《计算机测量与控制》 * |
| 芮伟，等: "暂冲式高速风洞流场控制系统建模与仿真", 《实验流体力学》 * |
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