CN108572054A - A kind of intermittent wind tunnel simulation experiment method and device - Google Patents
A kind of intermittent wind tunnel simulation experiment method and device Download PDFInfo
- Publication number
- CN108572054A CN108572054A CN201710148004.8A CN201710148004A CN108572054A CN 108572054 A CN108572054 A CN 108572054A CN 201710148004 A CN201710148004 A CN 201710148004A CN 108572054 A CN108572054 A CN 108572054A
- Authority
- CN
- China
- Prior art keywords
- parameter
- control
- wind
- unit
- simulation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to wind tunnel test simulation test fields.In view of the problems of the existing technology, a kind of intermittent wind tunnel simulation experiment method of present invention offer and device.For verification test flow, auxiliary adjust control parameter, reduce debugging risk be all very helpful, have the characteristics that easy to operate, perfect in shape and function, relevance grade are high.Simulation wind tunnel test is not only preferably realized, but also is also applied for newly into the correlation training of personnel.Control parameter auxiliary of the present invention adjusts the controlled parameter regulation characteristic curve function progress first derivation of fitting that step is obtained according to simulation unit step and obtains the proportional control factor k of controlled parameterp, by changing control parameter kpAnd ki, according to the controlled parameter simulation test effect of acquisition, the auxiliary that can complete control parameter after testing several times well adjusts work, and carrying out parameter tuning for follow-up practical blowing test provides basic foundation, wherein kpIt is that reference is changed with estimated value, kiIt is continuously increased since 0.
Description
Technical field
The present invention relates to wind tunnel test simulation test field, especially a kind of intermittent wind tunnel simulation experiment method and dress
It sets.
Background technology
Wind-tunnel is a kind of pipe-like experimental rig generating controllable uniform air flow, is research air flowing law, research boat
The ground-based simulation equipment of empty aerospace craft and other object aerodynamic characteristics.According to the difference of wind-tunnel drive form, wind-tunnel can divide
For diversified forms, intermittent wind tunnel therein is chosen herein as research object.
Intermittent wind tunnel control system mainly include operation management system, experimental flow field regulating system, data collecting system,
Data processing system and condition monitoring system etc..Before carrying out intermittent wind tunnel experiment, engineering staff needs not ventilate in equipment
In the case of, debugging confirmation is carried out to contents such as the experiment process of wind tunnel control system, test parameters and device talks first, is prevented
Only generation flow mistake, parameter give the problems such as unreasonable, equipment malfunction is made during actual tests, so as to cause test data
In vain, or even safety and risk are tested in initiation.Therefore it usually requires to introduce simulation experiment system in wind tunnel test, to improve
The economy of wind tunnel test and safety.Traditional wind tunnel simulation is in such a way that control system equipment is offline, i.e., each execution machine
Structure is not involved in simulative debugging, the movement merely with each equipment in wind comfort software emulation control system and controlled parameter
It adjusts.Therefore only it is able to verify that whether the compiling of Flow Field in Wind Tunnel control software and fundamental test flow are wrong, and can not access control ginseng
Whether number and flow field regulation strategy are reasonable and whether each equipment of system links normally.The above problem is debugged in wind tunnel simulation and is tried
It is the key that can further increase wind comfort level than more prominent during testing.
Invention content
The technical problem to be solved by the present invention is to：In view of the problems of the existing technology, a kind of intermittent wind tunnel is provided
Simulation experiment method and device.Control parameter is adjusted for verification test flow, auxiliary, reduction debugging risk has prodigious side
It helps, has the characteristics that easy to operate, perfect in shape and function, relevance grade are high.Not only preferably realize simulation wind tunnel test, Er Qieshi
For training the correlation newly into personnel.
The technical solution adopted by the present invention is as follows：
A kind of intermittent wind tunnel simulation experiment method includes：
Test process rate-determining steps：Test process control unit is according to the wind tunnel test control command of acquisition, control parameter
Collecting unit carries out data acquisition；Controlled motion control unit carries out On-line Control to each executing agency simultaneously；Test process control
Unit setting processed is controlled parameter objectives value, and wind comfort is carried out according to the control logic and strategy of setting；In experiment, parameter
Collecting unit measures each parameter of actuating mechanism of wind-tunnel；
Simulation unit step：Obtained control characteristic table and controlled parameter regulation characteristic curve letter are tested according to identification
Number, the corresponding wind-tunnel of each parameter of actuating mechanism information that calculating parameter collecting unit measurement obtains are controlled parameter value；
Control parameter auxiliary adjusts step：The controlled parameter regulation characteristic curve letter being fitted according to simulation unit step
Number carries out first derivation and obtains the proportional control factor k of controlled parameterp.By changing control parameter kpAnd ki, according to the quilt of acquisition
Parameter simulation test effect is controlled, the auxiliary that can complete control parameter after testing several times well adjusts work, is follow-up real
Border blowing test carries out parameter tuning and provides basic foundation, wherein kpIt is that reference is changed with estimated value, kiSince 0 constantly
Increase.
Further, a kind of intermittent wind tunnel simulation experiment method further includes wind tunnel operation management process：Pass through LabVIEW
Shared variable is created, network connection is created and realizes network share, reading permission, the write-in permission of shared variable are set；Variable is created
After building, test process control unit accesses the shared variable that wind tunnel operation administrative unit creates by communication unit；And parse wind
Wind tunnel test control command is obtained after the shared variable of hole operational management unit setting.
Further, the simulation unit module is surveyed to executing agency by discrimination method, more to obtain
A executing agency control characteristic table corresponding with controlled parameter；Multiple measurement by the table to same mechanism parameter, obtains
Repeatedly controlled parameter regulation characteristic, is fitted controlled parameter regulation characteristic curve function, calculating parameter collecting unit is measured with this
The corresponding wind-tunnel of each parameter of actuating mechanism information arrived is controlled parameter value.
Further, a kind of intermittent wind tunnel simulation experiment method further includes pattern displaying unit, receives parameter acquisition list
The various parameter values that member and simulation unit obtain, are realized by graphic interface and text box to each controlled parameter and executing agency
The real-time display of regulated quantity is realized and is shown to the visualization of wind comfort.
A kind of intermittent wind tunnel simulation test device includes：
Test process control unit：For the wind tunnel test control command according to acquisition, control parameter collecting unit carries out
Data acquire；Controlled motion control unit carries out On-line Control to each executing agency simultaneously；Test process control unit sets quilt
Parameter objectives value is controlled, wind comfort is carried out according to the control logic and strategy of setting；In experiment, parameter acquisition unit is to wind
Each parameter of actuating mechanism in hole measures；
Simulation unit：For testing obtained control characteristic table and controlled parameter regulation characteristic curve letter according to identification
Number, the corresponding wind-tunnel of each parameter of actuating mechanism information that calculating parameter collecting unit measurement obtains are controlled parameter value；
Control parameter auxiliary adjusts module：Controlled parameter regulation characteristic for being fitted according to simulation unit step is bent
Line function carries out first derivation and obtains the proportional control factor k of controlled parameterp.By changing control parameter kpAnd ki, according to acquisition
Controlled parameter simulation test effect, can complete the auxiliary of control parameter well after testing several times and adjust work, after being
Continuous practical blowing test carries out parameter tuning and provides basic foundation, wherein kpIt is that reference is changed with estimated value, kiSince 0
It is continuously increased.
Further, a kind of intermittent wind tunnel simulation test device further includes wind tunnel operation administrative unit：For passing through
LabVIEW creates shared variable, creates network connection and realizes network share, and reading permission, the write-in permission of shared variable is arranged；
After variable creates, test process control unit accesses the shared variable that wind tunnel operation administrative unit creates by communication unit；And
Wind tunnel test control command is obtained after the shared variable of parsing wind tunnel operation administrative unit setting.
Further, the simulation unit is surveyed to executing agency by discrimination method, and multiple hold is obtained with this
Row mechanism parameter control characteristic table corresponding with controlled parameter；Multiple measurement by the table to same mechanism parameter, obtains
Repeatedly controlled parameter regulation characteristic, is fitted controlled parameter regulation characteristic curve function, calculating parameter collecting unit is measured with this
The corresponding wind-tunnel of each parameter of actuating mechanism information arrived is controlled parameter value.
Further, a kind of intermittent wind tunnel simulation test device further includes pattern displaying unit, receives parameter acquisition list
The various parameter values that member and simulation unit obtain, are realized by graphic interface and text box to each controlled parameter and executing agency
The real-time display of regulated quantity is realized and is shown to the visualization of wind comfort.
In conclusion by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
In intermittent wind tunnel experiment, control parameter can be explored first in the case of no consumption of air source, with
Determine more accurately range and an influence relationship.Simultaneously because parameters simulation unit is based on wind-tunnel practical adjustments spy
Property, therefore when progress wind comfort, carry out parameter feedback using simulation unit and can be good at reflecting join controlled to reality
Several control characteristic, to embody the actual effect of the control parameter of selection well.Joined in this way by choosing different control
Number, the auxiliary that can complete control parameter after simulation test well several times adjusts work, for follow-up practical blowing test into
Row parameter tuning provides basic foundation.
It is set before wind comfort and is controlled parameter objectives value, then carry out wind-tunnel according to the control logic of setting and strategy
Simulation test.In experiment, the various kinds of sensors in system measures each executing agency's displacement of wind-tunnel, and simulation unit is utilized and obtained
Mechanism position information calculate wind-tunnel in real time and be controlled parameter value, absolute fix information and simulation parameter information forming position,
Parameter closed-loop control.Thus the adjusting of executing agency is introduced into simulation test, to realize to during actual tests
The simulation of control logic and strategy, the perfect emulation of wind tunnel test flow.
With the characteristic curve function obtained according to identification experiment, in wind comfort software, a simulation unit is increased newly,
The input of the unit be wind-tunnel executing agency position or aperture, export for wind-tunnel by control parameter (stagnation pressure, static pressure, injection pressure,
Mach number etc.).When carrying out simulation test, the observed pressure signal at wind-tunnel scene will be ignored, simulation unit output valve conduct
Feedback participates in the closed-loop control of each controlled parameter.
Another major function is the graphic software platform realized to wind comfort process.Traditional wind comfort
Graphic software platform be only capable of simply illustrating the communication condition between each system, therefore can not full simulation test process.The present invention exists
It is improved on original base, it, can be in real-time display simulation test in simulation test procedure by visualized graph interface
The situation of change of the motion conditions of each executing agency and every controlled parameter, dried to which the simulation of visual pattern is practical
Journey.Thus it is convenient for engineering staff to accurately hold wind tunnel test flow, control strategy in set-up procedure is debugged and tested to wind-tunnel
It whether accurately and reliably to be adjusted with control parameter, improves reliability and the safety of wind tunnel test.Meanwhile visual wind-tunnel is aobvious
Show that wind-tunnel control strategy is understood and appreciated in wind-tunnel personnel when function has been also convenient for technical training, convenient for opening for training
Exhibition.
Description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is intermittent wind tunnel simulation experiment method schematic diagram.
Fig. 2 is overall construction drawing.
Fig. 3 is test process control program flow diagram
Specific implementation mode
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification unless specifically stated can be equivalent or with similar purpose by other
Alternative features are replaced.That is, unless specifically stated, each feature is an example in a series of equivalent or similar characteristics
.
The present invention function module include：
1, test process control function
One of major function of the present invention is single action and the linkage control realized in simulation test to each executing agency of control system
System.In traditional wind comfort, the executing agency that control system is responsible for adjusting the controlled parameter such as stagnation pressure and Mach number adopts
The mode adjusted offline is taken, simulation test procedure is not involved in, and directly exports the stagnation pressure and Mach number of simulation by control system
Numerical value is used as the value of feedback of control system.The present invention realizes in simulation test procedure to each on the basis of original method
The independent control of a executing agency, while timing control can be carried out according to the experiment process set to multiple executing agencies,
The online linkage of implementation mechanism is adjusted.In this way, the reliability of each mechanism independently moving control can be not only verified,
The equipment fault for preventing practical blowing from occurring in the process, and complete wind tunnel simulation emulation can be adjusted to by linkage and provided
Hardware foundation.
2, copying
One of the major function of the present invention is to carry out full simulation emulation to wind tunnel test flow.Wind tunnel test flow refers to
Each executing agency of wind tunnel control system combines according to specific control strategy according to test requirements document link during the test
Process.The experiment process of design can be verified using practical blowing test, but frequent blowing task can not expire
The requirement of sufficient debugging test economy, while the experiment process of mistake may cause certain security risks.Therefore usually exist
Flow Field in Wind Tunnel is debugged and before formal test, needs to confirm experiment process control in the way of simulation test.
Traditional simulation test Row control is carried out by the way of control system executing agency off-line simulation, can not be complete
Reflection actual tests flow variation.When simulation test starts, control system sends flow field to measuring system and stablizes letter
Number, measuring system and then the simulation test flow for completing setting.It only realizes in this manner between each system of wind-tunnel
Communication joint debugging, and can not accurately simulate the detailed process of Flow Field in Wind Tunnel adjusting, also cannot achieve to system control strategy and
The verification of parameter.
The adjusting of each executing agency of control system is included in simulation test by the present invention for former methodical deficiency.
Concrete methods of realizing is as follows：
1) identification experiment.Identification experiment be obtain special test state under system actuator to be controlled parameter regulation characteristic
Process.By taking wind-tunnel main pressure regulator valve mechanism controls wind-tunnel stagnation pressure as an example, under conditions of other conditions all have determined, to obtain
Valve need to be navigated to a certain aperture, obtains this and open the control characteristic of stagnation pressure by main pressure regulator valve aperture under mechanism DA SA
Corresponding stable stagnation pressure pressure value is spent, then runs valve with fixed step, each ladder of acquisition after pressure stabilisation is corresponding
Stagnation pressure value.A series of apertures and steady pressure data near goal pressure are thus obtained, calculating of taking this as a foundation obtains certain
Valve control characteristic curve function P under state0=f (Pair,Sf,N,Sv), wherein P0For pressure, PairFor bleed pressure, SfRefer to for grid
Position, N are nozzle contour, SvFor valve opening.
2) simulation unit establishment step.According to the characteristic curve function that identification experiment obtains, in wind comfort software
In, increase a simulation unit newly, the input of the unit is wind-tunnel executing agency position or aperture, is exported as wind-tunnel by control parameter
(stagnation pressure, static pressure, injection pressure, Mach number etc.).When carrying out simulation test, the observed pressure signal at wind-tunnel scene will be neglected
Slightly, simulation unit output valve participates in the closed-loop control of each controlled parameter as feedback.
3) simulation test step.Obtained data are tested according to identification, sets and is controlled parameter objectives value, then according to setting
Fixed control logic and strategy carries out wind comfort.In experiment, the various kinds of sensors in system is to each executing agency of wind-tunnel
Displacement measures, and simulation unit calculates wind-tunnel using the mechanism position information of acquisition and is controlled parameter value, absolute fix in real time
Information and simulation parameter information forming position, parameter closed-loop control.Thus the adjusting of executing agency is introduced into simulation test,
To realize the simulation to control logic during actual tests and strategy, the perfect emulation of wind tunnel test flow.
4) control parameter assists setting function.Another of the invention major function be for control parameter assist it is whole
It is fixed.Include mainly controlled device, controller and feedback element in automatic control system.The closed loop characteristic of system is largely
The upper performance depending on controller, and the performance of controller is the selection of control parameter after all.Traditional temporarily rushes formula wind
Hole simulation experiment method since each executing agency is in off-line mode, can not each executing agency of accurate simulation control
Effect.Engineering staff can only be adjusted and be verified to the control parameter of setting by multiple practical blowing test, be increased
Debugging cost is added, while unreasonable control parameter may cause control system that security risks occur, and influence wind-tunnel just
Often operation.
For this problem, the present invention realizes the auxiliary setting function to control parameter, still with the control of main pressure regulator valve mechanism
For wind-tunnel stagnation pressure processed.The emulation that the controlled parameter regulation characteristic curve function obtained in the process using System Discrimination experiment is established
Unit passes through due to containing the variation relation between mechanism position information and the controlled parameter information of wind-tunnel and is controlled parameter
Regulating characteristic curve function can obtain stagnation pressure and often change the required valve position correction amounts of 1kPa, can estimate first accordingly
The control parameter k of stagnation pressure closed loopp(kp=f ' (Pair,Sf,N,Sv)).Simultaneously when carrying out simulation test, wind tunnel control system is each
Executing agency's coordinated signals under the United Dispatching of controller in simulation experiment system, since parameters simulation unit is based on wind
Hole practical adjustments characteristic, therefore carry out parameter feedback using simulation unit and can be good at reflecting the adjusting to practical controlled parameter
Characteristic, to embody the actual effect of the control parameter of selection well.In this way by changing control parameter (kpIt is with estimated value
With reference to being changed, kiIt is continuously increased since 0), it, can after testing several times according to the controlled parameter simulation test effect of acquisition
Auxiliary to complete control parameter well adjusts work, for follow-up practical blowing test progress parameter tuning provide substantially according to
According to.
5) graphic software platform function.Another major function of this patent is the figure realized to wind comfort process
Change display function.The various parameter values that pattern displaying unit receives parameter acquisition unit and simulation unit obtains, by graphical
Interface and text box are realized to the real-time display of each controlled parameter and executing agency's regulated quantity, are realized to wind comfort
Visualization display.
Traditional simulation test due to can not full simulation test process, original graphic software platform is only capable of simply showing
Communication condition between each system of wind-tunnel of anticipating.The present invention is improved on the original basis, by visualized graph interface, is being simulated
It, can be with the variation feelings of the motion conditions of each executing agency in real-time display simulation test and every controlled parameter during experiment
Condition, to the practical blowing process of simulation of visual pattern.Thus it is convenient for engineering staff to debug and test set-up procedure in wind-tunnel
Whether middle accurate assurance wind tunnel test flow, control strategy and control parameter adjust accurate and reliable, and improve wind tunnel test can
By property and safety.Meanwhile visual wind-tunnel display function has been also convenient for wind-tunnel personnel when technical training and has controlled plan to wind-tunnel
It is slightly understood and appreciated, is convenient for the development of training.
To realize the major function of above-mentioned intermittent wind tunnel simulation test, following methods and device are devised：
1, wind tunnel operation administrative unit
Wind tunnel operation administrative unit is that the host computer software of command scheduling is used in wind tunnel test, which is used for
The scheduling and management of wind comfort system, Flow Field in Wind Tunnel control system and other common apparatus status informations, the system are logical
Communication connection is often established by network and wind tunnel simulation system, be primarily adapted for use in control parameter and sensor coefficient download and on
It passes.In order to realize the unification of development platform in a certain range, systemic software development platform is unified for NI companies by us
LabVIEW selects the network share variable engine of LabVIEW as net to realize the decoupling of network communication and application software
Network communication middleware, is primarily adapted for use in that status information is read and single operation order is assigned.
Operational management software and the visioning procedure of each device talk in wind comfort system are：
A. network share variable is created：The network share variable for needing to communicate is created in wind comfort system, this
Network share variable can be some certain type of variable, can also be the data type based on self-defined control.Setting should
The reading of variable, write-in permission, after variable creates, the terminal of gain access can access the variable.
B. network connection is created：The network connection be directed toward and be accessed object is created in operational management module, which connects
Connect the address for being directed toward shared variable.
C. it reads, data is written：According to the access rights of variable, behaviour is written and read using variable reading and writing function pair variable
Make.
2, motion control unit
Simulation test motion control unit mainly realizes the single action and coordinated signals to each executing agency of wind-tunnel.Temporarily rush formula wind
The main controlled device in hole includes main pressure regulator valve system, bypass pressure regulation valve system, injection pressure regulation valve system, Shan Zhi mechanisms, the angle of attack
The parts such as mechanism.Each system control function and mode are essentially identical, below by taking main pressure regulator valve system as an example, introduce motion control list
The control method of member.
Main pressure regulator valve system control object includes main pressure regulator valve, main pressure regulator valve quick valve, main pressure regulator valve quick valve equalizing valve；
The extreme position switching value of main pressure regulator valve system monitoring include main pressure regulator valve standard-sized sheet/fully closed, pneumatic quick valve standard-sized sheet of main pressure regulator valve/
Fully closed, main pressure regulator valve quick valve equalizing valve standard-sized sheet/fully closed；Main pressure regulator valve system monitoring analog quantity includes main pressure regulator valve displacement, steady
Determine section stagnation pressure, test section static pressure, main pressure regulator valve downstream pressure, bleed pressure, atmospheric pressure etc..Its major control function includes：
A. main pressure regulator valve positioning function (speed, position, restraining position)；
B. main pressure regulator valve positions abort function；
C. main pressure regulator valve point operation control function (speed, direction)；
D. main pressure regulator valve back to zero control function；
E. main pressure regulator valve driver enable/goes to enable；
F. main pressure regulator valve driver malfunction resets；
G. main pressure regulator valve motor internal contracting brake/declutch；
H. main pressure regulator valve quick valve on/off operation；
I. main pressure regulator valve quick valve equalizing valve on/off operation.
The key step of implementation mechanism motion control includes：
1) data input：
Control parameter derives from wind tunnel operation management module, and the command content of input includes：
A. locating speed：Linear module is mm/s, and velocity accuracy 1mm/s, desin speed effective range is 0~30mm/
s；
B. position location：Linear module is mm, and positional precision 0.2mm, position effective range is 0~300mm；
C. orientation：Forward direction is the direction that valve is opened, and negative sense is the direction that valve closes；
D. restraining position：Linear module is mm, and effective range is 0~300mm；
E. action executes：Boolean quantity control instruction, when the instruction is changed into True by False, the corresponding positioning of execution,
Valve opening enables, action of declutching, and when instruction is changed into False by True, executes opposite action；Inching button hold mode
Lower execution corresponding actions then act cancellation after button release.
3, parameter acquisition unit
To realize that the closed loop of controlled parameter each to wind-tunnel is adjusted, need to measure each parameter in real time.Parameter acquisition
Unit is directed to actual demand in wind-tunnel, and multiple sensors is selected to be acquired corresponding parameter.The sensor used is shown in Table 1 institute
Show.
1 intermittent wind tunnel simulation test parameter acquisition table of table
4, simulation unit
Simulation unit obtains the control characteristic of each executing agency by system identifying method first, simulation of taking this as a foundation
The adjusting situation of practical controlled parameter.When each executing agency is adjusted in motion control unit, simulation unit adopts parameter
The mechanism displacement amount of collection unit feedback is converted into controlled parameter value in real time, in this, as the value of feedback of controlled parameter, realizes parameter
Closed-loop control.
Specific implementation method includes following sections content:
A. it is imitative stagnation pressure to be used as by System Discrimination experiment acquisition main pressure regulator valve system and bypass pressure regulator valve system adjustment characteristic
True unit；
B. acquisition injection pressure regulator valve system adjustment characteristic is tested by System Discrimination and is used as injection Pressure Simulation unit；
C. acquisition Shan Zhi mechanisms control characteristic is tested by System Discrimination and is used as Mach number simulation unit.
5 test process control units
Test process control unit is mainly responsible for the management of process in simulation test.Unit is according to the simulation test work of setting
Condition sends control instruction according to corresponding experiment process to motion control unit, to which implementation mechanism single action controls, Yi Jifeng
Hole preparation drives, starts experiment, measuring system acquires, acquisition finishes, becomes next ladder, normally cut-off, promptly cut-off, testing knot
The control of the process status such as beam.Control flow chart is as shown in Figure 3.
Test process control unit concrete methods of realizing is：
It receiving after wind tunnel operation administrative unit assigns " prepare drive " order, test process enters preparation start-up, into
Equipment state inspection before row experiment, determines ER equipment ready of participating in the experiment；" it will prepare to drive " to order simultaneously to be forwarded to wind-tunnel mould
Other units in quasi- pilot system.
Test it is ready, receive operational management unit transmission " drivings " order after, test process be transferred to test in shape
State, stream field stable state are judged, flow field stable state is sent out, and after receiving measuring system acquisition, continue to become next
Test process after the completion of testing ladder, is switched to pass by ladder to be managed to experiment ladder according to current test operating mode
Vehicle process.
After each subelement cut-offs according to requirement of cut-offfing, test process is transferred to off-test state, and resets various
Parameter is to default conditions.The invention is not limited in specific implementation modes above-mentioned.The present invention expands to any in this specification
The new feature of middle disclosure or any new combination, and disclose any new method or process the step of or any new group
It closes.
Claims (8)
1. a kind of intermittent wind tunnel simulation experiment method, it is characterised in that including：
Test process rate-determining steps：Test process control unit is according to the wind tunnel test control command of acquisition, control parameter acquisition
Unit carries out data acquisition；Controlled motion control unit carries out On-line Control to each executing agency simultaneously；Test process control is single
Member setting is controlled parameter objectives value, and wind comfort is carried out according to the control logic and strategy of setting；In experiment, parameter acquisition
Unit measures each parameter of actuating mechanism of wind-tunnel；
Simulation unit step：Obtained control characteristic table and controlled parameter regulation characteristic curve function, meter are tested according to identification
It calculates the corresponding wind-tunnel of each parameter of actuating mechanism that parameter acquisition unit measurement obtains and is controlled parameter value；
Control parameter auxiliary adjusts step：The controlled parameter regulation characteristic curve function being fitted according to simulation unit step into
Row first derivation obtains the proportional control factor k of controlled parameterp.By changing control parameter kpAnd ki, according to the controlled ginseng of acquisition
Digital-to-analogue intends test effect, and the auxiliary that can complete control parameter after testing several times well adjusts work, subsequently actually to blow
Wind experiment carries out parameter tuning and provides basic foundation, wherein kpIt is that reference is changed with estimated value, kiIt is continuously increased since 0.
2. a kind of intermittent wind tunnel simulation experiment method according to claim 1, it is characterised in that further include wind tunnel operation
Management process：Wind tunnel operation administrative unit creates shared variable by LabVIEW, creates network connection and realizes network share, if
Set reading permission, the write-in permission of shared variable；After variable creates, test process control unit accesses wind-tunnel by communication unit
The shared variable that operational management unit creates；And obtain wind tunnel test after parsing the shared variable of wind tunnel operation administrative unit setting
Control command.
3. a kind of intermittent wind tunnel simulation experiment method according to claim 1, it is characterised in that the simulation unit mould
Block is surveyed to executing agency by discrimination method, special to obtain the adjusting corresponding with controlled parameter of multiple executing agencies
Property table；Multiple measurement by the table to same mechanism parameter is obtained repeatedly being controlled parameter regulation characteristic, is fitted with this controlled
Parameter regulation characteristic curve function, the corresponding wind-tunnel quilt of each parameter of actuating mechanism information that calculating parameter collecting unit measurement obtains
Control parameter value.
4. a kind of intermittent wind tunnel simulation experiment method according to one of claims 1 to 3, it is characterised in that further include figure
Shape display unit receives the various parameter values of parameter acquisition unit and simulation unit acquisition, passes through graphic interface and text box
It realizes to the real-time display of each controlled parameter and executing agency's regulated quantity, realizes and the visualization of wind comfort is shown.
5. a kind of intermittent wind tunnel simulation test device, it is characterised in that including：
Test process control unit：For the wind tunnel test control command according to acquisition, control parameter collecting unit carries out data
Acquisition；Controlled motion control unit carries out On-line Control to each executing agency simultaneously；The controlled ginseng of test process control unit setting
Number scale value carries out wind comfort according to the control logic and strategy of setting；In experiment, parameter acquisition unit is each to wind-tunnel
Parameter of actuating mechanism measures；
Simulation unit：For according to the obtained control characteristic table of experiment and controlled parameter regulation characteristic curve function is recognized, counting
It calculates the corresponding wind-tunnel of each parameter of actuating mechanism information that parameter acquisition unit measurement obtains and is controlled parameter value；
Control parameter auxiliary adjusts module：Controlled parameter regulation characteristic curve letter for being fitted according to simulation unit step
Number carries out first derivation and obtains the proportional control factor k of controlled parameterp.By changing control parameter kpAnd ki, according to the quilt of acquisition
Parameter simulation test effect is controlled, the auxiliary that can complete control parameter after testing several times well adjusts work, is follow-up real
Border blowing test carries out parameter tuning and provides basic foundation, wherein kpIt is that reference is changed with estimated value, kiSince 0 constantly
Increase.
6. a kind of intermittent wind tunnel simulation test device according to claim 5, it is characterised in that further include wind tunnel operation
Administrative unit：For creating shared variable by LabVIEW, creates network connection and realize network share, shared variable is set
Read permission, write-in permission；After variable creates, test process control unit accesses wind tunnel operation administrative unit by communication unit
The shared variable of establishment；And obtain wind tunnel test control command after parsing the shared variable of wind tunnel operation administrative unit setting.
7. a kind of intermittent wind tunnel simulation test device according to claim 5, it is characterised in that the simulation unit is
Executing agency is surveyed by discrimination method, it is special to obtain the adjusting corresponding with controlled parameter of multiple parameter of actuating mechanism with this
Property table；Multiple measurement by the table to same mechanism parameter is obtained repeatedly being controlled parameter regulation characteristic, is fitted with this controlled
Parameter regulation characteristic curve function, the corresponding wind-tunnel quilt of each parameter of actuating mechanism information that calculating parameter collecting unit measurement obtains
Control parameter value.
8. a kind of intermittent wind tunnel simulation test device according to one of claim 5 to 7, it is characterised in that further include figure
Shape display unit receives the various parameter values of parameter acquisition unit and simulation unit acquisition, passes through graphic interface and text box
It realizes to the real-time display of each controlled parameter and executing agency's regulated quantity, realizes and the visualization of wind comfort is shown.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710148004.8A CN108572054B (en) | 2017-03-13 | 2017-03-13 | Temporary-impulse type wind tunnel simulation test method and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710148004.8A CN108572054B (en) | 2017-03-13 | 2017-03-13 | Temporary-impulse type wind tunnel simulation test method and device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108572054A true CN108572054A (en) | 2018-09-25 |
| CN108572054B CN108572054B (en) | 2020-01-07 |
Family
ID=63578582
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710148004.8A Active CN108572054B (en) | 2017-03-13 | 2017-03-13 | Temporary-impulse type wind tunnel simulation test method and device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108572054B (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207904A (en) * | 2020-01-02 | 2020-05-29 | 北京航天测控技术有限公司 | Wind tunnel test method, device and equipment based on VR and computer readable medium |
| CN111738627A (en) * | 2020-08-07 | 2020-10-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test scheduling method and system based on deep reinforcement learning |
| CN112068612A (en) * | 2020-09-14 | 2020-12-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel operation safety shutdown control method based on configuration mode |
| CN112069446A (en) * | 2020-08-28 | 2020-12-11 | 中国空气动力研究与发展中心计算空气动力研究所 | Wind tunnel group high-pressure air resource scheduling method and system |
| CN112304554A (en) * | 2020-12-02 | 2021-02-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for improving practicability of characteristic curve of air-vent valve of annular gap of wind tunnel |
| CN112346360A (en) * | 2020-11-09 | 2021-02-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel test flow verification method for mixed execution of actual operation and simulation |
| CN113280992A (en) * | 2021-07-19 | 2021-08-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel virtual flight test system for lifting body model |
| CN113375897A (en) * | 2021-05-26 | 2021-09-10 | 北京航空航天大学 | Modeling simulation method for temporary impulse type wind tunnel system |
| CN114912301A (en) * | 2022-07-18 | 2022-08-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel full-machine model force measurement test data processing and correcting system |
| CN114936477A (en) * | 2022-07-22 | 2022-08-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel operation and flow field control system design method based on WorkFlow |
| CN116296219A (en) * | 2023-05-24 | 2023-06-23 | 中国航空工业集团公司沈阳空气动力研究所 | Precise control method for temporary impact transonic wind tunnel target Mach number and rapid pressure |
| CN116382178A (en) * | 2023-06-05 | 2023-07-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Full-hydraulic servo driving control method for profile of jet pipe of large high-speed wind tunnel |
| CN117874400A (en) * | 2024-03-13 | 2024-04-12 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Aircraft model dynamic derivative test data processing system |
| CN117874400B (en) * | 2024-03-13 | 2024-06-04 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Aircraft model dynamic derivative test data processing system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202886998U (en) * | 2012-09-25 | 2013-04-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device |
| 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 |
| CN103135624A (en) * | 2012-12-19 | 2013-06-05 | 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 temporary flush type supersonic velocity wind tunnel with ejector function |
| CN104932565A (en) * | 2015-06-04 | 2015-09-23 | 中国空气动力研究与发展中心高速空气动力研究所 | High-precision temporary punching type injecting transonic speed wind tunnel flow field control structure |
-
2017
- 2017-03-13 CN CN201710148004.8A patent/CN108572054B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202886998U (en) * | 2012-09-25 | 2013-04-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Temporary punching type hypersonic wind tunnel model angle of incidence redundancy control device |
| 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 |
| CN103135624A (en) * | 2012-12-19 | 2013-06-05 | 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 temporary flush type supersonic velocity wind tunnel with ejector function |
| CN104932565A (en) * | 2015-06-04 | 2015-09-23 | 中国空气动力研究与发展中心高速空气动力研究所 | High-precision temporary punching type injecting transonic speed wind tunnel flow field control structure |
Non-Patent Citations (3)
| Title |
|---|
| 李平等: "2m×2m超声速风洞测量***与运行管理***研制", 《实验流体力学》 * |
| 芮伟等: "暂冲式高速风洞流场控制***建模与仿真", 《实验流体力学》 * |
| 褚卫华等: "2m×2m超声速风洞流场控制策略研究与实现", 《实验流体力学》 * |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207904A (en) * | 2020-01-02 | 2020-05-29 | 北京航天测控技术有限公司 | Wind tunnel test method, device and equipment based on VR and computer readable medium |
| CN111738627A (en) * | 2020-08-07 | 2020-10-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test scheduling method and system based on deep reinforcement learning |
| CN111738627B (en) * | 2020-08-07 | 2020-11-27 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test scheduling method and system based on deep reinforcement learning |
| CN112069446B (en) * | 2020-08-28 | 2022-04-01 | 中国空气动力研究与发展中心计算空气动力研究所 | Wind tunnel group high-pressure air resource scheduling method and system |
| CN112069446A (en) * | 2020-08-28 | 2020-12-11 | 中国空气动力研究与发展中心计算空气动力研究所 | Wind tunnel group high-pressure air resource scheduling method and system |
| CN112068612A (en) * | 2020-09-14 | 2020-12-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel operation safety shutdown control method based on configuration mode |
| CN112068612B (en) * | 2020-09-14 | 2022-10-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel operation safety shutdown control method based on configuration mode |
| CN112346360A (en) * | 2020-11-09 | 2021-02-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel test flow verification method for mixed execution of actual operation and simulation |
| CN112346360B (en) * | 2020-11-09 | 2021-05-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel test flow verification method for mixed execution of actual operation and simulation |
| CN112304554A (en) * | 2020-12-02 | 2021-02-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for improving practicability of characteristic curve of air-vent valve of annular gap of wind tunnel |
| CN112304554B (en) * | 2020-12-02 | 2022-07-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for improving practicability of characteristic curve of annular gap pressure regulating valve of wind tunnel |
| CN113375897A (en) * | 2021-05-26 | 2021-09-10 | 北京航空航天大学 | Modeling simulation method for temporary impulse type wind tunnel system |
| CN113280992A (en) * | 2021-07-19 | 2021-08-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel virtual flight test system for lifting body model |
| CN114912301A (en) * | 2022-07-18 | 2022-08-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Low-speed wind tunnel full-machine model force measurement test data processing and correcting system |
| CN114936477A (en) * | 2022-07-22 | 2022-08-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel operation and flow field control system design method based on WorkFlow |
| CN114936477B (en) * | 2022-07-22 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel operation and flow field control system design method based on WorkFlow |
| CN116296219A (en) * | 2023-05-24 | 2023-06-23 | 中国航空工业集团公司沈阳空气动力研究所 | Precise control method for temporary impact transonic wind tunnel target Mach number and rapid pressure |
| CN116296219B (en) * | 2023-05-24 | 2023-08-04 | 中国航空工业集团公司沈阳空气动力研究所 | Precise control method for temporary impact transonic wind tunnel target Mach number and rapid pressure |
| CN116382178A (en) * | 2023-06-05 | 2023-07-04 | 中国空气动力研究与发展中心高速空气动力研究所 | Full-hydraulic servo driving control method for profile of jet pipe of large high-speed wind tunnel |
| CN116382178B (en) * | 2023-06-05 | 2023-08-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Full-hydraulic servo driving control method for profile of jet pipe of large high-speed wind tunnel |
| CN117874400A (en) * | 2024-03-13 | 2024-04-12 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Aircraft model dynamic derivative test data processing system |
| CN117874400B (en) * | 2024-03-13 | 2024-06-04 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Aircraft model dynamic derivative test data processing system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108572054B (en) | 2020-01-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108572054A (en) | A kind of intermittent wind tunnel simulation experiment method and device | |
| CN111505964B (en) | Full-real information source semi-physical simulation system and test method for aircraft engine | |
| CN104142676B (en) | For testing the test device of virtual controlling instrument | |
| US7257523B1 (en) | Integrated distributed process control system functionality on a single computer | |
| CN103488098B (en) | The rapid prototyping method of aeroengine control system | |
| CN108344579A (en) | The semi physical verification method and system of aerial engine air passage component fault diagnosis | |
| US7987707B2 (en) | Wind tunnel with a model arranged therein, particularly a model of an aircraft, for acquiring and evaluating a plurality of measuring data, as well as method | |
| CN104699068A (en) | Universal simulator for aircraft engines | |
| PH12017000197A1 (en) | Plant builder system with integrated simulation and control system configuration | |
| CN103038714B (en) | The method of simulation industrial process, trace simulation device and automated system | |
| CN108803571A (en) | ECU desktop hardware assemblage on-orbits test system and hardware-in-the-loop test system | |
| CN103699743B (en) | CPS (cyber physical system) modeling and verifying method based on conversion from CPS-ADL (architecture description language) model into hybrid program | |
| CN111666648A (en) | Method for simulating dynamic characteristics of aircraft engine | |
| WO2000041050A1 (en) | Testing device for industrial control systems | |
| CN110119591B (en) | Oil motor simulation device | |
| CN107300860A (en) | A kind of Simulation of Aeroengine Control System platform courses object online change method | |
| CN208399988U (en) | The test macro and test device of vehicle electronic stability system | |
| CN106168760B (en) | Uncertain time-delayed systems determination of stability method based on convex polyhedron fault model | |
| CN114383879B (en) | Test method of second-order differential loop in flight simulator identification test guidance system | |
| CN116220921A (en) | Method for generating dynamic characteristic evaluation index of executing mechanism of spout control loop | |
| CN212229443U (en) | Full-real information source semi-physical simulation system of aircraft engine | |
| CN209148311U (en) | Cabinet type unit test device and control cabinet | |
| Marcos | Application of H-infinity fault diagnosis to ADDSAFE benchmark: the control surface jamming case | |
| Litt et al. | Evaluation of an outer loop retrofit architecture for intelligent turbofan engine thrust control | |
| CN207397000U (en) | The trailing suction hopper dredger power-equipment signal simulation device pushed away based on the double paddle bilaterals of two-shipper |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |