CN105181291A - Flow field test apparatus for hypersonic propulsion wind tunnel - Google Patents
Flow field test apparatus for hypersonic propulsion wind tunnel Download PDFInfo
- Publication number
- CN105181291A CN105181291A CN201510561070.9A CN201510561070A CN105181291A CN 105181291 A CN105181291 A CN 105181291A CN 201510561070 A CN201510561070 A CN 201510561070A CN 105181291 A CN105181291 A CN 105181291A
- Authority
- CN
- China
- Prior art keywords
- linear module
- wind tunnel
- field test
- flow
- pressure rake
- 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.)
- Pending
Links
Abstract
The invention discloses a flow field test apparatus for a hypersonic propulsion wind tunnel. The apparatus comprises a total pressure rake (6) for measuring flow field pressure, and further comprises a support frame (7), a double-shaft simultaneous movement system and a motion control system. The motion control system comprises a programmable logic controller (PLC), a motion controller, a first servo driver and a second servo driver; the double-shaft simultaneous movement system comprises a first servo motor (1) and a first linear module (4) which are at a first shaft and a second servo motor and a second linear module which are at a second shaft; the total pressure rake (6) is installed on a total pressure rake support (5), the first side of the total pressure rake support (5) is installed on the first linear module and the second side of the total pressure rake support is installed on the second linear module; the support frame (7) is fixed on an experiment chamber of the hypersonic propulsion wind tunnel, and the center of the support frame is coaxial with a jet pipe; and two shafts of the double-shaft simultaneous movement system are respectively installed in parallel at the left side and the right side of the support frame, and simultaneous movement of the first linear module (3) and the second linear module are executed through the motion control system so that parallelism of vertical tangent planes of the total pressure rake and the jet pipe is guaranteed.
Description
Technical field
The invention belongs to the technical field of hypersonic propulsion wind tunnel, relate to a kind of flow-field test device for hypersonic propulsion wind tunnel particularly, the fluid field pressure being mainly used in carrying out Flow Field in Wind Tunnel scan-type is measured.
Background technology
Hypersonic propulsion wind tunnel carries out the requisite equipment of hypersonic aircraft ground experiment.All will through a large amount of ground experiments in the development process of each course of new aircraft.Hypersonic propulsion wind tunnel is primarily of well heater, jet pipe, Laboratory Module, injector, engine mockup support system composition.Well heater supply a model test needed for high temperature and high pressure gas; Gas accelerates to required Mach number by jet pipe and enters Laboratory Module; Laboratory Module domestic demand maintains the corresponding atmospheric conditions of flying height, namely certain pressure environment; And injector is used for ensureing the low-pressure state in Laboratory Module.
In wind tunnel experiment, in order to ensure the reliability of experimental data, the quality in experiment flow field will meet the requirement of experiment of engine.Therefore before engine test, must measure nozzle flow field quality.At present in hypersonic wind tunnel field, fixed metering system is generally adopted for nozzle flow field pressure survey.The pressure survey can only carrying out a position once tested by single measurement framed bent.Many rows bent structure is complicated, easily affects nozzle flow field, causes experimental data inaccurate.And due to measuring position relatively fixing, cause the limitation of measurement data.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of flow-field test device for hypersonic propulsion wind tunnel is provided, it can be interrupted cross section, nozzle exit flow field or the measurement of continuous print scan-type, increase work efficiency, accurate measurement Flow Field in Wind Tunnel pressure distribution, do not affect wind-tunnel to start, and to the damage of stagnation pressure rake when preventing wind-tunnel start and stop.
Technical solution of the present invention is: this flow-field test device for hypersonic propulsion wind tunnel, it comprises stagnation pressure rake (6) measuring fluid field pressure, and this flow-field test device also comprises bracing frame (7), Biaxial synchronous kinematic system, kinetic control system; Kinetic control system comprises programmable logic controller (PLC) PLC, motion controller, the first servo-driver, the second servo-driver; Biaxial synchronous kinematic system is included in the first servomotor (1), the first linear module (4) of the first axle, and at the second servomotor, the second linear module of the second axle; Stagnation pressure rake is arranged on stagnation pressure rake support (5), and the first side of stagnation pressure rake support is arranged on the first linear module and the second side and is arranged on the second linear module; Bracing frame (7) is fixed on the Laboratory Module of hypersonic propulsion wind tunnel, its center and jet pipe coaxial cable; Two axles parallel left and right sides being installed on bracing frame respectively of Biaxial synchronous kinematic system, performs the first linear module by kinetic control system, being synchronized with the movement of the second linear module ensures that stagnation pressure rake is parallel with longitudinal tangent plane of jet pipe.
The present invention performs the first linear module by kinetic control system, being synchronized with the movement of the second linear module ensures that stagnation pressure rake is parallel with longitudinal tangent plane of jet pipe, thus accurately measures Flow Field in Wind Tunnel pressure distribution; The present invention adopts scan-type kinetic measurement, when same single test, jet pipe can be carried out to the measurement of continuous print or discontinuous, increase work efficiency; Stagnation pressure rake can be moved to nozzle exit with external position before wind-tunnel starts and after off-test by the present invention, and all wind-tunnel that do not affect start when preventing again wind-tunnel start and stop the damage that stagnation pressure is harrowed.
Accompanying drawing explanation
Fig. 1 is the front view according to the flow-field test device for hypersonic propulsion wind tunnel of the present invention.
Fig. 2 is the side view according to the flow-field test device for hypersonic propulsion wind tunnel of the present invention.
Fig. 3 is the circuit theory diagrams according to the flow-field test device for hypersonic propulsion wind tunnel of the present invention.
Embodiment
As Figure 1-3, this flow-field test device for hypersonic propulsion wind tunnel, it comprises stagnation pressure rake (6) measuring fluid field pressure, and this flow-field test device also comprises bracing frame (7), Biaxial synchronous kinematic system, kinetic control system; Kinetic control system comprises programmable logic controller (PLC) PLC, motion controller, the first servo-driver, the second servo-driver; Biaxial synchronous kinematic system is included in the first servomotor (1), the first linear module (4) of the first axle, and at the second servomotor, the second linear module of the second axle; Stagnation pressure rake (6) is arranged on stagnation pressure rake support (7), and the first side of stagnation pressure rake support is arranged on the first linear module and the second side and is arranged on the second linear module; Bracing frame is fixed on the Laboratory Module of hypersonic propulsion wind tunnel, its center and jet pipe coaxial cable; Two axles parallel left and right sides being installed on bracing frame respectively of Biaxial synchronous kinematic system, performs the first linear module by kinetic control system, being synchronized with the movement of the second linear module ensures that stagnation pressure rake is parallel with longitudinal tangent plane of jet pipe.
The present invention performs the first linear module by kinetic control system, being synchronized with the movement of the second linear module ensures that stagnation pressure rake is parallel with longitudinal tangent plane of jet pipe, thus accurately measures Flow Field in Wind Tunnel pressure distribution; The present invention adopts scan-type kinetic measurement, when same single test, jet pipe can be carried out to the measurement of continuous print or discontinuous, increase work efficiency; Stagnation pressure rake can be moved to nozzle exit with external position before wind-tunnel starts and after off-test by the present invention, and all wind-tunnel that do not affect start when preventing again wind-tunnel start and stop the damage that stagnation pressure is harrowed.
In addition, described stagnation pressure rake is yi word pattern stagnation pressure rake, and described stagnation pressure rake support is yi word pattern support.Stagnation pressure rake and the stagnation pressure rake support of other form can certainly be adopted.
In addition, the front on-deck of support frame as described above and Laboratory Module is coplanar.As shown in Figure 2.
In addition, the described first linear module, the second linear module all have double helix push rod and all install grating scale, and described first servomotor, the second servomotor all have photoelectric encoder.Grating scale is for detecting the kinematic accuracy of linear module, and its feedback position is as the positional information of experiment measuring point, and precision reaches micron order.The double helix push rod that linear module carries and the photoelectric encoder that servomotor carries make linear module have high precision.
In addition, described first servomotor, the second servomotor are rated power 0.4KW, Motor torque 1.28NM, Rated motor rotating speed 3000RPM.Control Biaxial synchronous kinematic system by PLC, ensure that the longitudinal tangent plane of stagnation pressure rake and nozzle flow field is parallel, it is 300mm/s that stagnation pressure can be made to harrow movement velocity.
In addition, the described first linear module, the second linear module are all with travel switch.The first linear module can be guaranteed like this, the slide block of the second linear module all can not cross stroke motion.
In addition, described kinetic control system also comprises pulpit main frame, and it is connected with PLC and is positioned over outside Laboratory Module.Be convenient to operated from a distance like this, and the safety of operating personnel can be ensured better.
The above; it is only preferred embodiment of the present invention; not any pro forma restriction is done to the present invention, every above embodiment is done according to technical spirit of the present invention any simple modification, equivalent variations and modification, all still belong to the protection domain of technical solution of the present invention.
Claims (7)
1. the flow-field test device for hypersonic propulsion wind tunnel, it comprises stagnation pressure rake (6) measuring fluid field pressure, it is characterized in that: this flow-field test device also comprises bracing frame (7), Biaxial synchronous kinematic system, kinetic control system; Kinetic control system comprises programmable logic controller (PLC) PLC, motion controller, the first servo-driver, the second servo-driver; Biaxial synchronous kinematic system is included in the first servomotor (1), the first linear module (6) of the first axle, and at the second servomotor, the second linear module of the second axle; Stagnation pressure rake (6) is arranged on stagnation pressure rake support (5), and the first side of stagnation pressure rake support is arranged on the first linear module and the second side and is arranged on the second linear module; Bracing frame is fixed on the Laboratory Module of hypersonic propulsion wind tunnel, its center and jet pipe coaxial cable; Two axles parallel left and right sides being installed on bracing frame respectively of Biaxial synchronous kinematic system, performs the first linear module by kinetic control system, being synchronized with the movement of the second linear module ensures that stagnation pressure rake is parallel with longitudinal tangent plane of jet pipe.
2. the flow-field test device for hypersonic propulsion wind tunnel according to claim 1, is characterized in that: described stagnation pressure rake (6) is yi word pattern stagnation pressure rake, and described stagnation pressure rake support is yi word pattern support.
3. the flow-field test device for hypersonic propulsion wind tunnel according to claim 2, is characterized in that: support frame as described above (7) is coplanar with the front on-deck of Laboratory Module.
4. the flow-field test device for hypersonic propulsion wind tunnel according to claim 3, it is characterized in that: the described first linear module, the second linear module all have double helix push rod (3) and all install grating scale (2), and described first servomotor (1), the second servomotor all have photoelectric encoder.
5. the flow-field test device for hypersonic propulsion wind tunnel according to claim 4, is characterized in that: described first servomotor, the second servomotor are rated power 0.4KW, Motor torque 1.28NM, Rated motor rotating speed 3000RPM.
6. the flow-field test device for hypersonic propulsion wind tunnel according to claim 5, is characterized in that: the described first linear module, the second linear module are all with travel switch.
7. the flow-field test device for hypersonic propulsion wind tunnel according to any one of claim 1-6, is characterized in that: described kinetic control system also comprises pulpit main frame, it is connected with PLC and is positioned over outside Laboratory Module.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510561070.9A CN105181291A (en) | 2015-09-06 | 2015-09-06 | Flow field test apparatus for hypersonic propulsion wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510561070.9A CN105181291A (en) | 2015-09-06 | 2015-09-06 | Flow field test apparatus for hypersonic propulsion wind tunnel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105181291A true CN105181291A (en) | 2015-12-23 |
Family
ID=54903533
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510561070.9A Pending CN105181291A (en) | 2015-09-06 | 2015-09-06 | Flow field test apparatus for hypersonic propulsion wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105181291A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107702881A (en) * | 2017-11-08 | 2018-02-16 | 苏州大学 | Wind-tunnel wind resistance tests locating platform and its control system |
| CN108332938A (en) * | 2018-05-17 | 2018-07-27 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of continuous wind tunnel two-freedom traverse measurement mechanism |
| CN109029899A (en) * | 2017-06-08 | 2018-12-18 | 航空航天工业部第六0研究所机械厂 | A kind of device in the accurate simulated engine nacelle flow field of energy |
| CN112556979A (en) * | 2021-02-22 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Synchronous rotation control device and method for upper and lower turnplates of wind tunnel test section |
| CN114486156A (en) * | 2021-12-28 | 2022-05-13 | 中国航天空气动力技术研究院 | Environmental wind tunnel flow field calibration and measurement system |
| CN116754176A (en) * | 2023-08-22 | 2023-09-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Online accurate estimation method for air source pressure of temporary flushing type high-speed wind tunnel |
| CN109029899B (en) * | 2017-06-08 | 2024-04-16 | 航空航天工业部第六0一研究所机械厂 | Device capable of accurately simulating flow field of nacelle of engine |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201118372Y (en) * | 2007-11-09 | 2008-09-17 | 大连光洋科技工程有限公司 | Bus intelligent electromotor |
| CN101701865A (en) * | 2009-11-20 | 2010-05-05 | 中国航空工业空气动力研究院 | Large tunnel traverse measuring device and installing and debugging method thereof |
| CN202002789U (en) * | 2011-03-23 | 2011-10-05 | 中国人民解放军国防科学技术大学 | Connection structure of supersonic spray pipe and test chamber |
| CN103398835A (en) * | 2013-08-21 | 2013-11-20 | 中国人民解放军国防科学技术大学 | System and method for testing transient air film cooling heat flow on basis of hypersonic-velocity gun air tunnel |
| CN203310603U (en) * | 2013-06-25 | 2013-11-27 | 中国航天空气动力技术研究院 | Moveable measuring mechanism for high-speed wind tunnel |
| CN103712769A (en) * | 2014-01-17 | 2014-04-09 | 中国航空工业集团公司哈尔滨空气动力研究所 | Wind tunnel wide-range direction field mobile measuring device |
| CN103969022A (en) * | 2014-05-23 | 2014-08-06 | 厦门大学 | Indirect measuring method for hypersonic speed wind tunnel turbulence scale |
| CN104359649A (en) * | 2014-10-17 | 2015-02-18 | 北京航天益森风洞工程技术有限公司 | Movable correcting device for common hypersonic-velocity wind tunnel |
| CN204202846U (en) * | 2014-09-30 | 2015-03-11 | 中国航天科技集团公司第六研究院第十一研究所 | A kind of total pressure measurement rake |
| CN104819822A (en) * | 2015-04-20 | 2015-08-05 | 中国科学院力学研究所 | Support system of hypersonic propulsion wind tunnel model |
-
2015
- 2015-09-06 CN CN201510561070.9A patent/CN105181291A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201118372Y (en) * | 2007-11-09 | 2008-09-17 | 大连光洋科技工程有限公司 | Bus intelligent electromotor |
| CN101701865A (en) * | 2009-11-20 | 2010-05-05 | 中国航空工业空气动力研究院 | Large tunnel traverse measuring device and installing and debugging method thereof |
| CN202002789U (en) * | 2011-03-23 | 2011-10-05 | 中国人民解放军国防科学技术大学 | Connection structure of supersonic spray pipe and test chamber |
| CN203310603U (en) * | 2013-06-25 | 2013-11-27 | 中国航天空气动力技术研究院 | Moveable measuring mechanism for high-speed wind tunnel |
| CN103398835A (en) * | 2013-08-21 | 2013-11-20 | 中国人民解放军国防科学技术大学 | System and method for testing transient air film cooling heat flow on basis of hypersonic-velocity gun air tunnel |
| CN103712769A (en) * | 2014-01-17 | 2014-04-09 | 中国航空工业集团公司哈尔滨空气动力研究所 | Wind tunnel wide-range direction field mobile measuring device |
| CN103969022A (en) * | 2014-05-23 | 2014-08-06 | 厦门大学 | Indirect measuring method for hypersonic speed wind tunnel turbulence scale |
| CN204202846U (en) * | 2014-09-30 | 2015-03-11 | 中国航天科技集团公司第六研究院第十一研究所 | A kind of total pressure measurement rake |
| CN104359649A (en) * | 2014-10-17 | 2015-02-18 | 北京航天益森风洞工程技术有限公司 | Movable correcting device for common hypersonic-velocity wind tunnel |
| CN104819822A (en) * | 2015-04-20 | 2015-08-05 | 中国科学院力学研究所 | Support system of hypersonic propulsion wind tunnel model |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109029899A (en) * | 2017-06-08 | 2018-12-18 | 航空航天工业部第六0研究所机械厂 | A kind of device in the accurate simulated engine nacelle flow field of energy |
| CN109029899B (en) * | 2017-06-08 | 2024-04-16 | 航空航天工业部第六0一研究所机械厂 | Device capable of accurately simulating flow field of nacelle of engine |
| CN107702881A (en) * | 2017-11-08 | 2018-02-16 | 苏州大学 | Wind-tunnel wind resistance tests locating platform and its control system |
| CN107702881B (en) * | 2017-11-08 | 2024-01-05 | 苏州大学 | Wind tunnel wind-resistant experiment positioning platform and control system thereof |
| CN108332938A (en) * | 2018-05-17 | 2018-07-27 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of continuous wind tunnel two-freedom traverse measurement mechanism |
| CN108332938B (en) * | 2018-05-17 | 2024-04-19 | 中国航空工业集团公司沈阳空气动力研究所 | Two-degree-of-freedom movement measuring mechanism of continuous wind tunnel |
| CN112556979A (en) * | 2021-02-22 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Synchronous rotation control device and method for upper and lower turnplates of wind tunnel test section |
| CN114486156A (en) * | 2021-12-28 | 2022-05-13 | 中国航天空气动力技术研究院 | Environmental wind tunnel flow field calibration and measurement system |
| CN116754176A (en) * | 2023-08-22 | 2023-09-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Online accurate estimation method for air source pressure of temporary flushing type high-speed wind tunnel |
| CN116754176B (en) * | 2023-08-22 | 2023-10-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Online accurate estimation method for air source pressure of temporary flushing type high-speed wind tunnel |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105181291A (en) | Flow field test apparatus for hypersonic propulsion wind tunnel | |
| CN104111138B (en) | A kind of large-scale missile propulsive plant six component force and calibrating installation | |
| CN102607799B (en) | Device for changing Mach number in supersonic velocity wind tunnel model experiment and working method | |
| CN104990683B (en) | One kind segmentation type micro hinge moment balance | |
| CN104318107A (en) | Method for acquiring high-precision atmosphere data of aircraft flying across atmospheric layer | |
| CN203083802U (en) | Flow measuring and controlling experiment device practical for aviation/aerospace | |
| Shun et al. | Rapid prototyping of aerodynamics research models | |
| CN104776861B (en) | Flexible calibration device for calibrating wind tunnel vision measurement system | |
| CN102692312B (en) | Quasi-three-dimensional automatic measurement system for wind tunnels of atmospheric boundary layer | |
| JP6288675B2 (en) | Kinematic characteristic measuring device and kinematic characteristic measuring method | |
| CN209230910U (en) | A kind of quick Ce Yapa mechanism for wind tunnel test | |
| CN103033334A (en) | Testing device of flow measurement and control used in aerospace | |
| CN106596032A (en) | Variable Mach number nozzle mechanism having large-stroke range and high precision | |
| CN102749181A (en) | Wind tunnel test method on basis of momentum theory | |
| CN204556213U (en) | Boiler cold-state aerodynamic field on-line measurement device | |
| CN207600320U (en) | A kind of device of simulant missile aerodynamic loading loading | |
| CN204903126U (en) | A flow control device for low speed wind tunnel TPS is experimental | |
| CN104359445A (en) | Serial movement mechanism parameter error measuring device and method based on pull rope encoder | |
| CN106768801A (en) | A kind of double rotary shaft yaw angle converting means of high accuracy for wind tunnel test | |
| CN103530441A (en) | Method for three-dimensional modeling of steam turbine set through three-dimensional laser scanning technology | |
| CN101852629A (en) | Ultrasonic flow sensor array for channels or river channels and arrangement method thereof | |
| Cartieri | Experimental investigations on the Common Research Model at ONERA-S2MA | |
| CN103674470B (en) | PIV flow field velocity modification method | |
| CN108519211A (en) | Wind-tunnel Wind measurement system and method | |
| CN110879128B (en) | Test model and method for obtaining front edge heat flux density |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151223 |