CN108388281A - The closed loop reflux of injection driving temporarily rushes formula supersonic wind tunnel flow field control method - Google Patents
The closed loop reflux of injection driving temporarily rushes formula supersonic wind tunnel flow field control method Download PDFInfo
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- CN108388281A CN108388281A CN201810539925.1A CN201810539925A CN108388281A CN 108388281 A CN108388281 A CN 108388281A CN 201810539925 A CN201810539925 A CN 201810539925A CN 108388281 A CN108388281 A CN 108388281A
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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
- G05D16/2026—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 with a plurality of throttling means
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- 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
Temporarily formula supersonic 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, in return valve, additional-air inlet pressure regulator valve, under the cooperation of exhaust shutter, establish stable supersonic flow field, accurately controlling for stable section stagnation pressure is realized wherein under injector pressure regulator valve and additional-air inlet pressure regulator valve collective effect, on this basis, the supersonic flow field that stable different M numbers are established under the same operation stagnation pressure can be realized in temporarily rushing formula supersonic wind tunnel under the cooperation in nozzle contour and diffusion segment type face.The present invention can effectively widen the operation envelope curve and simulation context of wind-tunnel in the simulation for temporarily rushing realization negative pressure operating condition in formula supersonic wind tunnel that closed loop flows back.The stagnation pressure that stable section needed for supersonic flow field is established when can significantly reduce the high M numbers of traditional intermittent wind tunnel simultaneously, advantageously reduces the aerodynamic loading of model.Be conducive to improve wind-tunnel balance measurement precision.
Description
Technical field
It is the present invention relates to temporarily formula supersonic 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 supersonic wind tunnel is temporarily rushed with half reflux of 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.
It is general to require in order to ensure the gas flowed through in wind-tunnel pipeline can smoothly be discharged into ambient atmosphere for high-speed wind tunnel
Static pressure outline when gas is discharged into air is higher than external environment atmospheric pressure (being normally referred to as back-pressure), due to external environment atmospheric pressure
Change small, it is believed that it is relative constant, it can thus be assumed that wind-tunnel back-pressure is relative constant.For supersonic wind tunnel, simulation is different
Supersonic flow field need wind-tunnel to reach institute when establishing supersonic speed on the basis of given nozzle contour and diffusion segment type face
The minimal pressure ratio needed, could establish supersonic flow field, and with the increase of M numbers, required pressure ratio also gradually increases, and M numbers are higher, pressure
The amplification of ratio dramatically increases.
In order to meet above-mentioned requirements, wind tunnel test efficiency is improved, wind tunnel operation cost is reduced, realizes wind-tunnel in same stagnation pressure
Realize that the supersonic flow field of different M numbers, the western developed countries such as USA and Europe use continuous wind tunnel scheme, the mating multistage in wind-tunnel
Axial Flow Compressor provides required pressure ratio condition as driving.And the country does not have the warp for establishing continuous type ultrasonic speed wind-tunnel also
It tests, still using the design scheme for temporarily rushing formula supersonic wind tunnel.It temporarily rushes in formula supersonic wind tunnel, since external atmosphere pressure is
It is metastable, that is to say it is metastable when the back-pressure of wind-tunnel, therefore in order to meet the supersonic flow field for establishing different M numbers
It needs, needs to control the stagnation pressure in wind-tunnel stable section to meet the needs of required pressure ratio.To temporarily rush formula supersonic wind tunnel when M numbers by
1.5 increase to 4.5, and the stable section stagnation pressure of corresponding wind-tunnel will will increase by 10 times or so.Difference M numbers need different stagnation pressures simultaneously.Mesh
Before, the supersonic flow field of stable different M numbers how is established in the case where realizing same stagnation pressure in temporarily rushing formula supersonic wind tunnel, both at home and abroad
All lack successful experience for using for reference.
Invention content
It is an object of the invention to：Temporarily rushing formula supersonic wind tunnel and cannot be established under same stagnation pressure surely for closed loop reflux
The problem of supersonic flow field of fixed different M numbers, provide a kind of closed loop reflux of injection driving temporarily rushes formula supersonic wind tunnel stream
Field control method.The hypervelocity subsonic airflow that this method is ejected by the injector after diffuser is used as main driving, is adjusted in reflux
Under the collective effect for saving valve, exhaust shutter, the steady flow of air-flow in wind-tunnel circuit is realized, and pass through additional-air inlet pressure regulator valve
It realizes accurately controlling for wind-tunnel stable section stagnation pressure, can temporarily be rushed in formula supersonic wind tunnel what closed loop flowed back by above-mentioned control method
Realize the test capability for the supersonic flow field that stable different M numbers are established 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
Temporarily rush formula supersonic wind tunnel flow field control method, which is characterized in that include 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
Set aperture and exhaust throttle valve 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, exhaust throttle valve opening are preset to given target location；And open the shut-off valve of injector system and additional-air inlet system
And quick valve；Wherein, return valve, exhaust shutter are preset to by step 1 by servo hydraulic oil cylinder (or servo motor)
In give position aperture；
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, return valve is quickly opened to step
Aperture is given in rapid one, and opens the position aperture calculated in additional-air inlet pressure regulator valve to step 1, closed-loop control rapidly simultaneously
The target stagnation pressure given in stable section stagnation pressure to step 1, using stable section stagnation pressure as closed loop feed back object, closed-loop control
Additional-air inlet pressure regulation valve opening realizes the closed-loop control of stable section stagnation pressure；
Step 5: after stable section stagnation pressure reaches closed-loop control precision in step 4, that is, establish stable supersonic flow field；
Step 6: after completing blowing test by set flow, while to additional-air inlet pressure regulator valve and quick valve, reflux
Regulating valve assigns shutdown command, it is ensured that additional-air inlet pressure regulator valve and quick valve, return valve are closed；
Step 7: the relationship for judging stable section stagnation pressure between the target stagnation pressure that cut-offs, cut-offs if stable section stagnation pressure is more than
Target stagnation pressure, then after stable section stagnation pressure reaches and cut-offs target stagnation pressure, quick closedown injector pressure regulator valve and quick valve, and close
All shut-off valves of wind-tunnel complete complete blowing test flow；If stable section stagnation pressure is less than the target stagnation pressure that cut-offs, slowly close
Injection pressure regulator valve is closed, after stable section stagnation pressure reaches and cut-offs target stagnation pressure, quick closedown injector pressure regulator valve and quick valve, and close
All shut-off valves of wind-tunnel are closed, complete blowing test flow is completed.
Preferably, temporarily rushing formula supersonic wind tunnel includes：Reflux line；It is connected to the 4th turning on reflux line in turn
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
It is total to bring stagnation pressure, M numbers, injection into according to given operation stagnation pressure, experiment M numbers and bleed pressure for functional relation between valve opening
Pressure, return valve aperture, exhaust throttle valve opening, jet pipe segment type face, is spread in the function in segment type face at additional-air inlet stagnation pressure,
Calculate corresponding injection stagnation pressure, additional-air inlet stagnation pressure, return valve aperture, exhaust throttle valve opening, nozzle contour and expansion
Segment type face is dissipated, and stagnation pressure is brought into valve bit function according to injection stagnation pressure and additional-air inlet stagnation pressure, calculates corresponding injection tune
The position aperture of pressure valve and additional-air inlet pressure regulator valve, wherein specifically 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)；According to
P0 is steady=ξ × P0 is anti-
Calculate stable section stagnation pressure, in formula, P0 is steadyFor stable section stagnation pressure, P0 is anti-For wind-tunnel back-pressure, ξ is pressure ratio coefficient, and ξ is horse
The function of conspicuous number；According to
P02=(1+ ζ1+ζ2+…+ζn)P0 is steady
Calculate stagnation pressure after pressure regulator valve, in formula, P02For stagnation pressure after injection pressure regulator valve, ζnFor the pressure loss of n-th of section
Coefficient；According to
S=f (ε) × Smax, ε=P02/P01
Pressure regulation valve position aperture in calculating, in formula, P01For air source stagnation pressure, ε is pressure ratio before and after pressure regulator valve, and f (ε) is valve position
The functional relation between relative opening degree and pressure ratio is set, different M numbers f (ε) are different, SmaxValve maximum position aperture is represented, S is represented
Valve physical location aperture；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 increasing is drawn
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, FTP is 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/P01
Calculate the valve location aperture of auxiliary pressure-regulating valve.
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.
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.
Preferably, in step 4 under the premise of closed-loop control injector stagnation pressure, by quickly opening additional-air inlet
Pressure regulator valve and return valve make stable section be rapidly reached minimum operation stagnation pressure, can be quickly by shock wave push out test section, drop
The shock loading of low model.
Preferably, stable section stagnation pressure when being cut-off in step 7 by controlling wind-tunnel, can effectively reduce wind-tunnel
To the shock loading of model during cut-offfing.
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, is spread in the function in segment type face at jet pipe segment type face, calculates corresponding injection stagnation pressure, additional-air inlet stagnation pressure, reflux adjusting
Valve opening, exhaust throttle valve opening, nozzle contour and diffusion segment type face, and brought into always according to injection stagnation pressure and additional-air inlet stagnation pressure
Pressure calculates the position aperture of corresponding injection pressure regulator valve and additional-air inlet pressure regulator valve with valve bit function.
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 supersonic wind tunnel upgrade to diffuser rear portion suction temporarily rush formula supersonic wind tunnel.
(2) difference of closed loop reflux temporarily rushed formula supersonic wind tunnel and establish stabilization under same stagnation pressure may be implemented in the present invention
The supersonic flow field of M numbers has been broken in traditional limitation for temporarily rushing formula supersonic wind tunnel.
(3) present invention can be opened up the half backflow test operating mode of intermittent wind tunnel that traditional closed loop flows back by sub- transonic speed range
Open up supersonic range.
(4) present invention can be in the simulation for temporarily rushing realization negative pressure operating condition in formula supersonic wind tunnel that closed loop flows back, effectively
The operation envelope curve and simulation context of wind-tunnel are widened.Ultrasound is established when can significantly reduce the high M numbers of traditional intermittent wind tunnel simultaneously
The stagnation pressure of stable section needed for fast flow field, advantageously reduces the aerodynamic loading of model.Be conducive to improve wind-tunnel balance measurement essence
Accuracy.
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 supersonic 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, at the second turning in the second round corner section
Return valve system is configured between section and third round corner section, is turned the 5th and is configured a set of exhaust throttle between exhausting silencer tower
Valve system.
As shown in Figure 1, wind-tunnel primary air enters wind-tunnel pipe through injector admission line and valve system (injection pressure regulator valve)
In road, supersonic speed free jet is formed by injector 81 and is used as driving, air-flow is pushed successively to flow through the first round corner section 9, reflux
Pipeline I 16, the second round corner section 10 are simultaneously shunted in 12 position of return valve：A part of air-flow enters through return valve 12
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, nozzle section 4, examination
Test the reflux that section 5, brace sections 6, diffuser 7 and injector 81 form closed loop；Another part air-flow does not pass through return valve 12
It is directly discharged into air after flowing directly into the 5th round corner section 13, discharge duct 141, exhaust shutter 142 and exhausting silencer tower 143.
Wind-tunnel additional-air inlet flows directly into return duct by additional-air inlet pipeline 111, additional-air inlet pressure regulator valve 112 and return valve 12
Then road II 17 passes through third round corner section 15, reflux line III 18, the 4th round corner section 1, stable section 2, contraction section 3, nozzle section again
4, it mixes, repeats with the supersonic speed free jet that injector ejects after test section 5, brace sections 6, diffuser 7, injector 81
Above-mentioned flow path forms complete closed-loop flow, and so on forms stable flowing.Specific flow field control method is as follows：
Output nozzle contour location parameter is calculated according to operation stagnation pressure, experiment M numbers, bleed pressure before blowing, diffuser location parameter, is drawn
Emitter runs stagnation pressure and corresponding position aperture, additional-air inlet stagnation pressure and corresponding position aperture, return valve position aperture, exhaust
Throttle valve position aperture.Nozzle contour and diffusion segment type face are adjusted in place, and exhaust throttle valve opening is prefabricated to positioning
It sets.When blowing test, after opening injector pressure regulator valve to given position aperture, closed-loop control injector operating pressure works as injection
After device pressure reaches control accuracy, rapid return valve of opening opens additional-air inlet pressure regulator valve to given position aperture
To given position aperture, then using stable section stagnation pressure as feedback target, realized surely by controlling additional-air inlet pressure regulation valve opening
The closed-loop control for determining section stagnation pressure had both been set up stable supersonic flow field, had then been pressed after stable section stagnation pressure reaches control accuracy
Set blowing test flow progress wind-tunnel flyoff terminates up to experiment process, when then cut-offfing, judges stable section stagnation pressure
Wait for that stable section stagnation pressure reaches pass if stable section stagnation pressure is more than the target stagnation pressure that cut-offs with the relationship between the target stagnation pressure that cut-offs
After vehicle target stagnation pressure, quick closedown injector pressure regulator valve and quick valve, and all shut-off valves of wind-tunnel are closed, complete complete blowing
Experiment process；If stable section stagnation pressure is less than the target stagnation pressure that cut-offs, slowly closing injection pressure regulator valve waits for that stable section stagnation pressure reaches
After target of cut-offfing stagnation pressure, quick closedown injector pressure regulator valve and quick valve, and all shut-off valves of wind-tunnel are closed, completion is completely blown
Wind experiment process.It using control method provided by the invention, can be rushed in formula supersonic wind tunnel temporarily, realize that the same operation is total
The supersonic flow field of stable different M numbers is established in pressure.It breaches tradition and temporarily rushes formula supersonic wind tunnel different Mach number needs
The limitation of supersonic flow field could be established with different stable section stagnation pressures.It is total that wind-tunnel can be substantially reduced using the invention simultaneously
Pressure, ram compression, advantageously reduce wind-tunnel security risk, it is ensured that the safety of wind-tunnel and test model is conducive to the measurement for improving balance
Precision.
As shown in Figure 1, the effect of injection pressure regulator valve is according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure and injection tune
The functional relation of pressure valve aperture determines the position aperture of the valve, for controlling injection pressure and flow, and drives and leads as wind-tunnel
Air-flow, driving wind-tunnel loop gas flow form closed-loop flow.
As shown in Figure 1, the effect of return valve is adjusted with reflux according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure
The functional relation of section valve opening determines the position aperture of the valve, and wind-tunnel return duct is flowed into for controlling the incoming through the second round corner section
The flow in road II.
As shown in Figure 1, the effect of exhaust shutter is saved with exhaust according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure
The functional relation of stream valve opening determines the position aperture of the valve, for controlling the gas flow for flowing through exhaust shutter, to improve
The gas pressure of wind-tunnel return valve section.
As shown in Figure 1, the effect of additional-air inlet system is according to wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure and auxiliary
The functional relation of admission pressure and pressure regulation valve position aperture determines the position aperture of the pressure and the valve of additional-air inlet, for improving
The control accuracy of 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)；According to
P0 is steady=ξ × P0 is anti-
Calculate stable section stagnation pressure, in formula, P0 is steadyFor stable section stagnation pressure, P0 is anti-For wind-tunnel back-pressure, ξ is pressure ratio coefficient, and ξ is horse
The function of conspicuous number；According to
P02=(1+ ζ1+ζ2+…+ζn)P0 is steady
Calculate stagnation pressure after pressure regulator valve, in formula, P02For stagnation pressure after injection pressure regulator valve, ζnFor the pressure loss of n-th of section
Coefficient；According to
S=f (ε) × Smax, ε=P02/P01
Pressure regulation valve position aperture in calculating, in formula, P01For air source stagnation pressure, ε is pressure ratio before and after pressure regulator valve, and f (ε) is valve position
The functional relation between relative opening degree and pressure ratio is set, different M numbers f (ε) are different, SmaxValve maximum position aperture is represented, S is represented
Valve physical location aperture；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 increasing is drawn
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/P01
Calculate the valve location aperture of auxiliary pressure-regulating valve.
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 a kind of stream for temporarily rushing formula supersonic wind tunnel flow field control method of the closed loop reflux of injection driving of the present invention
Cheng Tu, 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.
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 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 and step 07：Additional-air inlet pressure regulator valve is opened to given aperture, closed-loop control stable section stagnation pressure；It beats simultaneously
Return valve is opened to given aperture.It is specific as follows：It controls program and passes through control room host computer remote control testing ground bottom
Machine assigns action command, and slave computer assigns open command by driver to return valve, and return valve is pressed step
Calculated position is opened in place in 02；And simultaneously, slave computer is assigned by driver to additional-air inlet pressure regulator valve servo-drive system
Open command, and additional-air inlet pressure regulator valve is opened in place by calculated position in step 02, then made with stable section stagnation pressure
For closed loop feed back object, the position aperture of closed-loop control additional-air inlet pressure regulator valve realizes the closed-loop control of stable section stagnation pressure
It is required that.
Step 08：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 09：Wind tunnel test is carried out by set blowing flow.It is specific as follows：When control system meets step 01 to step
After 08 control requires, it is transferred to flow of exactly drying.And be changed according to the model attitude angle given in step 02, measure depanning
Aerodynamic loading suffered by type.
Step 10：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 11 and step 12：Additional-air inlet pressure regulator valve and quick valve are closed, return valve is simultaneously closed off.Specifically such as
Under：Control program assigns action command by control room host computer remote control testing ground slave computer, and slave computer passes through driving
Device is assigned closing of cut-offfing to return valve servo-drive system and additional-air inlet pressure regulator valve servo-drive system and quick valve servo-drive system and is referred to
It enables.
Step 13：Judge whether additional-air inlet pressure regulator valve and quick valve and return valve close in place.Matched by it
The limit switch signal of set, judges whether above-mentioned valve closes in place, if closed in place, control system stops publication and cut-offs
Instruction, is transferred to next step；Conversely, continuing to send shutdown signal, until closing.
Step 14, step 15 and step 16：The relationship for judging stable section stagnation pressure between the target stagnation pressure that cut-offs, if stablized
Section stagnation pressure is more than cut-off target stagnation pressure, then after stable section stagnation pressure reaches and cut-offs target stagnation pressure, quick closedown injector pressure regulator valve
And quick valve, and all shut-off valves of wind-tunnel are closed, complete complete blowing test flow；If stable section stagnation pressure is less than the mesh that cut-offs
Stagnation pressure is marked, then slowly closing injection pressure regulator valve, after stable section stagnation pressure reaches and cut-offs target stagnation pressure, quick closedown injector pressure regulation
Valve and quick valve, and all shut-off valves of wind-tunnel are closed, complete complete blowing test flow.It is specific as follows：Control system passes through
The pressure of in-site measurement sensor acquisition is monitored the variation of stable section stagnation pressure, if stable section stagnation pressure is more than target of cut-offfing
Stagnation pressure, then control system continue keep injector closed-loop control, after stable section stagnation pressure reaches and cut-offs target stagnation pressure, control system
Quick closedown injector pressure regulator valve and quick valve instruction are assigned to slave computer, and closing life is assigned to each shut-off valve system of wind-tunnel
It enables；If stable section stagnation pressure is less than the target stagnation pressure that cut-offs, control system assigns slowly closing injection pressure regulator valve to slave computer
Instruction, after stable section stagnation pressure, which reaches, cut-offs target stagnation pressure, control system assigns quick closedown injector pressure regulator valve to slave computer
It is instructed with quick valve, and shutdown command is assigned to each shut-off valve system of wind-tunnel.
Step 17：Judge whether to close in place.It is specific as follows：According to ejection system quick valve, pressure regulator valve and shut-off valve
Limit switch judges whether valve closes in place, while being judged whether to close in place by the shut-off valve limit switch of each system,
If all closed in place, control system stops issuing instruction of cut-offfing, conversely, continuing to send instruction of cut-offfing, until closing.
Step 18：Terminate.After control system executes the step 01 to step 17, 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 (8)
1. a kind of closed loop reflux of injection driving temporarily rushes formula supersonic wind tunnel flow field control method, which is characterized in that including with
Lower step：
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 and exhaust throttle valve 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, row
Gas throttle valve opening is preset to given target location；And open the shut-off valve and quickly of injector system and additional-air inlet system
Valve；
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, while opening additional-air inlet pressure regulator valve and returning
Regulating valve, the target stagnation pressure given in closed-loop control stable section stagnation pressure to step 1 are flowed, and return valve is adjusted to step
It is calculated in one and gives target location；
Step 5: after stable section stagnation pressure reaches closed-loop control precision in step 4, that is, establish stable supersonic flow field；
Step 6: being adjusted after completing blowing test by set flow, while to additional-air inlet pressure regulator valve and quick valve, reflux
Valve assigns shutdown command, it is ensured that additional-air inlet pressure regulator valve and quick valve, return valve are closed；
Step 7: the relationship for judging stable section stagnation pressure between the target stagnation pressure that cut-offs, if stable section stagnation pressure is more than target of cut-offfing
Stagnation pressure, then after stable section stagnation pressure reaches and cut-offs target stagnation pressure, quick closedown injector pressure regulator valve and quick valve, and close wind-tunnel
All shut-off valves complete complete blowing test flow；If stable section stagnation pressure is less than the target stagnation pressure that cut-offs, slowly closing draws
Pressure regulator valve is penetrated, after stable section stagnation pressure reaches and cut-offs target stagnation pressure, quick closedown injector pressure regulator valve and quick valve, and close wind
All shut-off valves in hole complete complete blowing test flow.
2. the closed loop reflux of injection driving as described in claim 1 temporarily rushes formula supersonic wind tunnel flow field control method, special
Sign is that temporarily rushing formula supersonic wind tunnel includes：Reflux line；Be connected in turn the 4th round corner section on reflux line, stable section,
Contraction section, nozzle section, test section, brace sections, diffuser, injector system, the first round corner section, the second round corner 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 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 supersonic wind tunnel flow field control method, special
Sign is, needs to debug by wind-tunnel in step 1, establishes wind tunnel operation stagnation pressure, experiment M numbers, bleed pressure and injector pressure
Between power and corresponding valve location, additional-air inlet stagnation pressure and corresponding valve location, return valve aperture, exhaust throttle valve opening
Functional relation.
4. the closed loop reflux of injection driving as claimed in claim 2 temporarily rushes formula supersonic wind tunnel flow field control method, special
Sign is, 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 supersonic wind tunnel flow field control method, special
Sign is, the gas for flowing through discharge duct and being discharged in wind-tunnel reflux road is adjusted by controlling exhaust throttle valve opening in step 2
Body 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 supersonic wind tunnel flow field control method, special
Sign is, the supersonic flow that injector ejects in step 3 under the collective effect of return valve and exhaust shutter,
Air-flow is set to form steady and sustained flowing in wind-tunnel circuit.
7. the closed loop reflux of injection driving as claimed in claim 2 temporarily rushes formula supersonic wind tunnel flow field control method, special
Sign is, in step 4 under the premise of closed-loop control injector stagnation pressure, by quickly opening additional-air inlet pressure regulator valve and returning
Regulating valve is flowed, so that stable section is rapidly reached minimum operation stagnation pressure, rushing for model can be reduced quickly by shock wave push out test section
Hit load.
8. the closed loop reflux of injection driving as claimed in claim 2 temporarily rushes formula supersonic wind tunnel flow field control method, special
Sign is, stable section stagnation pressure when being cut-off in step 7 by controlling wind-tunnel, can effectively reduce during wind-tunnel cut-offs
To the shock loading of model.
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