CN110307958B - Device for measuring high-temperature plasma wind tunnel stagnation point instantaneous heat flow - Google Patents
Device for measuring high-temperature plasma wind tunnel stagnation point instantaneous heat flow Download PDFInfo
- Publication number
- CN110307958B CN110307958B CN201910599672.1A CN201910599672A CN110307958B CN 110307958 B CN110307958 B CN 110307958B CN 201910599672 A CN201910599672 A CN 201910599672A CN 110307958 B CN110307958 B CN 110307958B
- Authority
- CN
- China
- Prior art keywords
- wind tunnel
- heat flow
- graphite baffle
- plate
- low
- 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.)
- Active
Links
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 32
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 32
- 239000010439 graphite Substances 0.000 claims abstract description 32
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 238000005259 measurement Methods 0.000 description 8
- 239000000463 material Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 238000012360 testing method Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 238000000691 measurement method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 238000013142 basic testing Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000003019 stabilising effect Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Images
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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Plasma Technology (AREA)
Abstract
The application discloses a device for measuring high-temperature plasma wind tunnel stagnation point instantaneous heat flow, which is characterized by comprising a graphite baffle, a connecting fixing seat, a motor bracket, a low-speed motor, a rib plate, a support, a coaxial thermocouple, a clamping seat and a stable bottom plate.
Description
Technical Field
The invention belongs to the technical field of plasma wind tunnel measurement, and particularly relates to a device for measuring instantaneous heat flow on the surface of a test material in an arc plasma wind tunnel by using a contact measurement method.
Background
The planet reentry is the fourth stage of the complete flight of the aircraft, the flight speed of the aircraft is extremely high and can reach supersonic speed, the shock wave generated at the front end of the aircraft decomposes the gas flowing at the front edge to generate gas with high enthalpy and high ionization state, and the gas generates very serious test on the thermal protection performance of the aircraft.
The plasma wind tunnel is used as one of measuring equipment for checking the thermal protection system of the aircraft, and is widely applied to the test of the reentry aircraft thermal protection system due to the characteristic that the plasma wind tunnel can stably generate high-temperature and high-enthalpy plasma airflow for a long time.
In the plasma wind tunnel, the measurement of the related parameters of the surface of the material to be measured and the interior of the plasma airflow has important significance for successfully simulating the actual high-altitude flight state and researching the physicochemical interaction process of the high-enthalpy airflow and the thermal protection material. The coaxial thermocouple is one of basic test means for measuring high-temperature heat flow, belongs to a contact type measurement method, has the advantages of simple measurement principle, few error factors, high response speed and the like, and is an optimal instrument for measuring instantaneous heat flow. In the field of plasma wind tunnels, the surface material of the coaxial thermocouple cannot be stably solidified for a long time, so that a precedent for using the coaxial thermocouple for measuring transient airflow of the plasma wind tunnel is not provided.
Disclosure of Invention
The invention aims to design a measuring device for the standing point instantaneous heat flow of a high-temperature plasma wind tunnel, and measure the heat flow value of high-temperature airflow of the plasma wind tunnel on the surface of a material. The specific technical scheme of the invention is as follows:
a device for measuring the high-temperature plasma wind tunnel stagnation point instantaneous heat flow is characterized by comprising a graphite baffle, a connecting fixing seat, a motor bracket, a low-speed motor, a rib plate, a support, a coaxial thermocouple, a clamping seat and a stable bottom plate, wherein the graphite baffle is circular, a plurality of bolt holes are uniformly distributed in the graphite baffle, and an arc-shaped vent groove is formed in the graphite baffle; the connecting fixing seat is provided with a plurality of bolt holes which are evenly distributed and are matched with the bolt holes of the graphite baffle plate, and the graphite baffle plate is fixedly connected with one end of the connecting fixing seat through the bolt holes by bolts and nuts; the other end of the connecting fixed seat is connected with the low-speed motor through a flat key of the low-speed motor, and a connecting position is reinforced by using a screw; the low-speed motor is fixed on the motor bracket through a screw; the motor bracket is fixedly connected with the rib plate through bolts and nuts;
the coaxial thermocouple is arranged in the clamping seat in a press fit mode and is clamped through a bolt and a nut;
the clamping seat, the stable bottom plate and the rib plate are connected through bolts and nuts;
the ribbed plate is connected with the support through a bolt and a nut.
Preferably, the arc-shaped vent groove is concentric with the graphite baffle, the central angle is 45-120 degrees, and the width is 1-3 mm.
Preferably, the ribbed plate and the support are made of stainless steel, and the clamping seat is made of plastic.
The invention has the beneficial effects that:
1. the graphite baffle is driven by the low-speed motor, and the time and the interval of instantaneous airflow flowing through the coaxial thermocouple can be controlled by the vent groove according to different rotating speeds of the low-speed motor.
2. The coaxial thermocouple is prevented from being damaged by long-time ablation, and the purpose of instantaneous heat flow measurement can be achieved.
3. The graphite baffle and the low-speed motor are connected through the connecting fixing seat, so that the torque transmission of the low-speed motor is stable, and the rotating speed is uniform.
Drawings
In order to illustrate embodiments of the present invention or technical solutions in the prior art more clearly, the drawings which are needed in the embodiments will be briefly described below, so that the features and advantages of the present invention can be understood more clearly by referring to the drawings, which are schematic and should not be construed as limiting the present invention in any way, and for a person skilled in the art, other drawings can be obtained on the basis of these drawings without any inventive effort. Wherein:
FIG. 1 is a structural diagram of a device for measuring the stagnation instantaneous heat flow of a high-temperature plasma wind tunnel according to an embodiment of the invention;
FIG. 2 is a structural diagram of a device for measuring the stagnation instantaneous heat flow of a high-temperature plasma wind tunnel according to an embodiment of the invention;
FIG. 3 is a front view of a graphite baffle plate;
FIG. 4 is a view of the connection holder;
FIG. 5 is a front view and a side view of the holder;
FIG. 6 is a view showing a structure of a flat key.
The reference numbers illustrate:
101-a graphite baffle; 102-a motor mount; 103-a low speed motor; 104-a rib plate; 105-a stabilising baseplate; 106-a holder; 107-coaxial thermocouple; 201-connecting a fixed seat; 202-support.
Detailed Description
In order that the above objects, features and advantages of the present invention can be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings. It should be noted that the embodiments and features of the embodiments of the present application may be combined with each other without conflict.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described herein, and therefore the scope of the present invention is not limited by the specific embodiments disclosed below.
As shown in fig. 1 to 4, a device for measuring a stagnation point instantaneous heat flow of a high-temperature plasma wind tunnel is characterized by comprising a graphite baffle 101, a connecting fixing seat 201, a motor bracket 102, a low-speed motor 103, a rib plate 104, a support 202, a coaxial thermocouple 107, a clamping seat 106 and a stable bottom plate 105, wherein the graphite baffle 101 is circular, a plurality of bolt holes are uniformly distributed on the graphite baffle 101, and an arc-shaped vent groove is formed in the graphite baffle 101, and is used for blocking most high-temperature high-enthalpy airflow and intermittently releasing a small part of high-temperature gas to the coaxial thermocouple 107, so that a small amount of continuous airflow can be provided while a temperature measuring component is protected; a plurality of bolt holes which are uniformly distributed and are matched with the bolt holes of the graphite baffle plate 101 are formed in the connecting fixing seat 201, and the graphite baffle plate 101 is fixedly connected with one end of the connecting fixing seat 201 through the bolt holes through bolts and nuts; the other end of the connecting fixing seat 201 is connected with the low-speed motor 103 through a flat key of the low-speed motor 103, and the connecting position is reinforced by using a screw, so that the rotating speed of the graphite baffle plate 101 in the rotating process is stable, the centering performance is good, and the torque of the low-speed motor 103 can be stably transmitted to the graphite baffle plate 101.
The low-speed motor 103 is fixed on the motor bracket 102 through screws; the motor bracket 102 is firmly connected with the rib plate 104 through bolts and nuts.
The coaxial thermocouple 107 is arranged in the clamping seat 106 in a press fit mode, the exposed length of the coaxial thermocouple 107 is adjustable, and the coaxial thermocouple 107 is clamped through a bolt and a nut, so that the parameter measurement of the heat flux density of high-temperature airflow at different axial positions is completed, meanwhile, the long-time stable measurement is realized, and the defect that only short-time measurement can be carried out in the prior art is overcome.
The clamping seat 106, the stable bottom plate 105 and the rib plate 104 are connected through bolts and nuts; the rib 104 is connected to the support 202 by a bolt and a nut.
In some embodiments, the arcuate vent grooves are concentric with the graphite baffle 101, have a central angle of 45 ° to 120 °, and have a width of 1mm to 3 mm.
In some embodiments, the ribs 104 and the support 202 are stainless steel and the holder 106 is plastic.
The working principle of the device for measuring the high-temperature plasma wind tunnel stagnation point instantaneous heat flow is that when the graphite baffle plate 101 rotates, high-temperature high-enthalpy gas can continuously pass through the vent grooves in the graphite baffle plate 101 for a short time, and the rear coaxial thermocouple 107 receives heat flow impact to measure the temperature. The power starts and drives low-speed motor 103 and rotate, and low-speed motor 103 drives graphite baffle 101 through connecting fixing base 201 and rotates, and the air channel on graphite baffle 101 is at the rotation in-process and is interrupted through high-temperature gas, and coaxial thermocouple 107 contacts high-temperature gas and takes place heat conduction, converts the temperature variation into the signal of telecommunication and obtains temperature measurement data. The method can overcome the defect that the coaxial thermocouple 107 cannot measure the temperature for a long time under the condition of not losing the physical properties of the original gas working medium, and meanwhile, the characteristics of high response speed and high accuracy of the coaxial thermocouple 107 are fully utilized to finish the measurement of the heat flux density of the high-temperature high-enthalpy plasma gas flow.
In the present invention, the terms "first", "second", "third", and "fourth" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. The term "plurality" means two or more unless expressly limited otherwise.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. A device for measuring the high-temperature plasma wind tunnel stagnation point instantaneous heat flow is characterized by comprising a graphite baffle, a connecting fixed seat, a motor bracket, a low-speed motor, a ribbed plate, a support, a coaxial thermocouple, a clamping seat and a stable bottom plate, wherein,
the graphite baffle is circular, a plurality of bolt holes are uniformly distributed on the graphite baffle, and an arc-shaped vent groove is formed in the graphite baffle;
the connecting fixing seat is provided with a plurality of bolt holes which are evenly distributed and are matched with the bolt holes of the graphite baffle plate, and the graphite baffle plate is fixedly connected with one end of the connecting fixing seat through the bolt holes by bolts and nuts;
the other end of the connecting fixed seat is connected with the low-speed motor through a flat key of the low-speed motor, and a connecting position is reinforced by using a screw;
the low-speed motor is fixed on the motor bracket through a screw;
the motor bracket is fixedly connected with the rib plate through bolts and nuts;
the coaxial thermocouple is arranged in the clamping seat in a press fit mode and is clamped through a bolt and a nut;
the clamping seat, the stable bottom plate and the rib plate are connected through bolts and nuts;
the ribbed plate is connected with the support through a bolt and a nut.
2. The device for measuring the high-temperature plasma wind tunnel stagnation point instantaneous heat flow according to claim 1, wherein the arc-shaped vent groove is concentric with the graphite baffle, the central angle of the arc-shaped vent groove is 45-120 degrees, and the width of the arc-shaped vent groove is 1-3 mm.
3. The device for measuring the high-temperature plasma wind tunnel stagnation instantaneous heat flow according to claim 1 or 2, characterized in that the ribbed plate and the support are made of stainless steel, and the clamping seat is made of plastic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910599672.1A CN110307958B (en) | 2019-07-04 | 2019-07-04 | Device for measuring high-temperature plasma wind tunnel stagnation point instantaneous heat flow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910599672.1A CN110307958B (en) | 2019-07-04 | 2019-07-04 | Device for measuring high-temperature plasma wind tunnel stagnation point instantaneous heat flow |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110307958A CN110307958A (en) | 2019-10-08 |
| CN110307958B true CN110307958B (en) | 2020-05-12 |
Family
ID=68079001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910599672.1A Active CN110307958B (en) | 2019-07-04 | 2019-07-04 | Device for measuring high-temperature plasma wind tunnel stagnation point instantaneous heat flow |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110307958B (en) |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4309901A (en) * | 1979-12-18 | 1982-01-12 | The United States Of America As Represented By The Secretary Of The Air Force | Heat transfer calibration plate |
| JP2003065890A (en) * | 2001-08-23 | 2003-03-05 | Mitsubishi Heavy Ind Ltd | Wind tunnel device |
| CN101393071B (en) * | 2007-09-19 | 2010-12-22 | 中国科学院工程热物理研究所 | Visual observation and transient measurement method and apparatus for cooling process of turbine blade |
| CN101441114B (en) * | 2008-04-11 | 2010-07-14 | 哈尔滨工业大学 | Heat flow and kinetic pressure composite test device of plasma jet flow field |
| CN201740750U (en) * | 2010-03-11 | 2011-02-09 | 宝山钢铁股份有限公司 | Experimental device for measuring heat flow or heat exchange coefficient of thin strip continuous casting interface |
| CN103398835B (en) * | 2013-08-21 | 2016-01-06 | 中国人民解放军国防科学技术大学 | Based on gaseous film control transient heat flow test macro and the method for hypersonic gun wind tunnel |
| CN104792152B (en) * | 2015-04-29 | 2017-02-22 | 宁夏昇力恒真空设备有限公司 | High-temperature vacuum sintering furnace with automatic thermocouple plugging and unplugging device |
| CN105928973B (en) * | 2016-05-04 | 2019-10-25 | 清华大学合肥公共安全研究院 | A kind of experiment test system and method for protective garment thermal resistance |
| CN106706166B (en) * | 2016-11-14 | 2019-04-30 | 北京临近空间飞行器系统工程研究所 | The compound plug heat flow transducer of the ceramic wall surface of low-heat stream environment suitable for high enthalpy |
| CN106872725B (en) * | 2017-01-16 | 2019-07-05 | 北京航空航天大学 | A kind of flight probe for pulsed plasma thruster measurement |
| CN108151997B (en) * | 2017-11-29 | 2019-08-09 | 中国航天空气动力技术研究院 | A kind of stationary point hot-fluid and the common measuring device and measuring method of stagnation pressure |
| CN207703444U (en) * | 2017-12-28 | 2018-08-07 | 中国航天空气动力技术研究院 | A kind of airvane surface cold wall heat flow density and device for pressure measurement |
| CN108458852B (en) * | 2018-05-24 | 2024-03-29 | 中国航空工业集团公司沈阳空气动力研究所 | Rapid temperature and pressure changing device and temperature and pressure changing method for high-temperature wind tunnel |
| CN109580162B (en) * | 2018-12-20 | 2019-12-10 | 中国空气动力研究与发展中心超高速空气动力研究所 | high-enthalpy flow field heat flow measuring device used in strong electromagnetic environment |
-
2019
- 2019-07-04 CN CN201910599672.1A patent/CN110307958B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN110307958A (en) | 2019-10-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Stalder et al. | Heat transfer from a hemisphere-cylinder equipped with flow-separation spikes | |
| Sahoo et al. | Film cooling effectiveness on a large angle blunt cone flying at hypersonic speed | |
| CN110307958B (en) | Device for measuring high-temperature plasma wind tunnel stagnation point instantaneous heat flow | |
| Stickney | Recovery and time-response characteristics of six thermocouple probes in subsonic and supersonic flow | |
| CN109387349B (en) | Irregular antenna window surface heat flux density and pressure measuring device | |
| CN109556762A (en) | It is a kind of for measuring the probe of cavity heat flux distribution | |
| CN112577687A (en) | Pneumatic heat-vibration combined test device for small wing rudder structure | |
| CN214373222U (en) | Pneumatic heat-vibration combined test device for small wing rudder structure | |
| CN215115096U (en) | Arc wind tunnel variable angle flat plate narrow gap heat flow measurement test device | |
| CN210745590U (en) | Film heating device | |
| CN212692907U (en) | Measurement detection device with prevent spilling function | |
| CN213779139U (en) | Vortex flowmeter DSP frequency spectrum analysis gas device | |
| Hsieh et al. | Local heat transfer in a rotating square channel with jet impingement | |
| CN217878054U (en) | Temperature transmitter capable of rapidly radiating heat | |
| Hah et al. | Effect of rotation on a rotating hot-wire sensor | |
| JP2006162296A (en) | Impeller flow meter | |
| CN219536103U (en) | Network testing device | |
| Sandborn et al. | Heat loss from yawed hot wires at subsonic Mach numbers | |
| CN220751555U (en) | Surface heat flow measuring device for surface protrusions of wind tunnel test model | |
| CN216717453U (en) | Detection platform that suitability is high | |
| CN217669235U (en) | Fan quality testing uses operation panel | |
| CN112729593B (en) | Ultrasonic flowmeter large-range temperature measuring equipment and method for water pipe | |
| CN212156445U (en) | Clean room anemoscope support | |
| CN215641069U (en) | Novel digital display oxygen index tester | |
| CN219608822U (en) | Point heat source method liquid heat conductivity coefficient measuring device |
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 | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231013 Address after: 1408-003, 14th Floor, Shining Building, No. 35 Xueyuan Road, Haidian District, Beijing, 100191 Patentee after: Star Enthalpy Technology (Beijing) Co.,Ltd. Address before: 100191 No. 37, Haidian District, Beijing, Xueyuan Road Patentee before: BEIHANG University |