CN207351650U - A kind of small-sized wind tunnel stagnation point ablation experimental rig - Google Patents
A kind of small-sized wind tunnel stagnation point ablation experimental rig Download PDFInfo
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- CN207351650U CN207351650U CN201721071367.8U CN201721071367U CN207351650U CN 207351650 U CN207351650 U CN 207351650U CN 201721071367 U CN201721071367 U CN 201721071367U CN 207351650 U CN207351650 U CN 207351650U
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- plasma
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- air inlet
- arc heater
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- 238000002679 ablation Methods 0.000 title claims abstract description 14
- 238000001816 cooling Methods 0.000 claims abstract description 11
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 11
- 238000010891 electric arc Methods 0.000 claims abstract description 8
- 238000009413 insulation Methods 0.000 claims description 3
- 238000003475 lamination Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 abstract description 2
- 238000000034 method Methods 0.000 abstract description 2
- 238000004088 simulation Methods 0.000 abstract description 2
- 238000006243 chemical reaction Methods 0.000 abstract 1
- 108010066114 cabin-2 Proteins 0.000 description 5
- 238000002474 experimental method Methods 0.000 description 3
- 230000005611 electricity Effects 0.000 description 2
- 239000011825 aerospace material Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- Plasma Technology (AREA)
- Discharge Heating (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model discloses a kind of small-sized wind tunnel stagnation point ablation experimental rig, it is related to ablation test engineering device technique field.Lobe pump is connected with water cooling experimental cabin, water cooling experimental cabin is connected with plasma-arc heater, positive electrode and negative electrode are provided with plasma-arc heater, the first field coil is provided with positive electrode, the second field coil is provided with negative electrode, air inlet is provided with the middle part of plasma-arc heater, air inlet is internally provided with electric arc, and the end of air inlet is communicated with spout.Using lobe pump counterflow-preventing inlet duct, electric arc is coordinated to form superpower wind-tunnel pattern, wind speed adjustable extent：28 Mach；Lobe pump frequency control air quantity, determines frequency conversion amount according to arc temperature, forms stable high wind speed superhigh temperature flow field, the state of flight of complete real simulation aerospace craft, verifies the reliability of material used by aerospace flight instruments.
Description
Technical field
A kind of small-sized wind tunnel stagnation point ablation experimental rig is the utility model is related to, is specially ablation test device technique neck
Domain.
Background technology
It is intended to before the actual operation of aerospace material and auxiliary facility to do various experiments and ensures its security performance, it is existing
Small-sized wind tunnel stagnation point ablation experimental rig structure it is complex, volume is larger, and operate it is cumbersome, it is therefore desirable to study one
The small-sized wind-tunnel stationary point ablation test device of kind.
The content of the invention
The purpose of this utility model is to provide a kind of small-sized wind tunnel stagnation point ablation experimental rig, to solve above-mentioned background skill
Art there are the problem of.
To achieve the above object, the utility model provides following technical solution：A kind of small-sized wind tunnel stagnation point ablation experiment dress
Put and be connected including lobe pump 1, water cooling experimental cabin 2 and plasma-arc heater 3, lobe pump 1 with water cooling experimental cabin 2, water cooling examination
Hatch checking 2 is connected with plasma-arc heater 3, and the plasma-arc heater 3 includes positive electrode 3-1, the first magnetic field line
Enclose 3-2, air inlet 3-3, electric arc 3-4, insulation lamination 3-5, the second field coil 3-6, negative electrode 3-7 and spout 3-8, plasma
Positive electrode 3-1 and negative electrode 3-7 are provided with electro-arc heater 3, the first field coil 3-2, negative electricity are provided with positive electrode 3-1
It is provided with the second field coil 3-6 on the 3-7 of pole, the middle part of plasma-arc heater 3 is provided with air inlet 3-3, in air inlet 3-3
Portion is provided with electric arc 3-4, and the end of air inlet 3-3 is communicated with spout 3-8.
Preferably, the shell of the plasma-arc heater 3 is shielding sandwich type element.
Preferably, the outside of the plasma-arc heater 3 is provided with programmable controller 3-1, programmable control
Device 3-1 processed is connected with the control of plasma-arc heater 3.
Compared with prior art, the beneficial effects of the utility model are：Using lobe pump counterflow-preventing inlet duct, coordinate electricity
Arc forms superpower wind-tunnel pattern, wind speed adjustable extent：2-8 Mach；Lobe pump frequency control air quantity, determines to become according to arc temperature
Frequency is measured, and forms stable high wind speed superhigh temperature flow field, the state of flight of complete real simulation aerospace craft, verifies aerospace
The reliability of material used by flight instruments.
Brief description of the drawings
Fig. 1 is the utility model structure schematic elevation view；
Fig. 2 is the structure diagram of plasma-arc heater in the utility model.
Embodiment
The following is a combination of the drawings in the embodiments of the present utility model, and the technical scheme in the embodiment of the utility model is carried out
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are without making creative work
All other embodiments obtained, shall fall within the protection scope of the present invention.
- 2 are please referred to Fig.1, the utility model provides a kind of technical solution：A kind of small-sized wind tunnel stagnation point ablation experimental rig
Including lobe pump 1, water cooling experimental cabin 2 and plasma-arc heater 3, lobe pump 1 is connected with water cooling experimental cabin 2, water cooling experiment
Cabin 2 is connected with plasma-arc heater 3, and the plasma-arc heater 3 includes positive electrode 3-1, the first field coil
3-2, air inlet 3-3, electric arc 3-4, insulation lamination 3-5, the second field coil 3-6, negative electrode 3-7 and spout 3-8, plasma electric
Positive electrode 3-1 and negative electrode 3-7 are provided with arc heater 3, the first field coil 3-2, negative electrode are provided with positive electrode 3-1
It is provided with the second field coil 3-6 on 3-7, the middle part of plasma-arc heater 3 is provided with air inlet 3-3, inside air inlet 3-3
Electric arc 3-4 is provided with, the end of air inlet 3-3 is communicated with spout 3-8.
Preferably, the shell of the plasma-arc heater 3 is shielding sandwich type element.
Preferably, the outside of the plasma-arc heater 3 is provided with programmable controller 3-1, programmable control
Device 3-1 processed is connected with the control of plasma-arc heater 3.
While there has been shown and described that the embodiment of the utility model, for the ordinary skill in the art,
It is appreciated that these embodiments can be carried out with a variety of changes in the case where not departing from the principle of the utility model and spirit, repaiied
Change, replace and modification, the scope of the utility model are defined by the appended claims and the equivalents thereof.
Claims (3)
- A kind of 1. small-sized wind tunnel stagnation point ablation experimental rig, it is characterised in that：It include lobe pump (1), water cooling experimental cabin (2) and Plasma-arc heater (3), lobe pump (1) are connected with water cooling experimental cabin (2), and water cooling experimental cabin (2) adds with plasma-arc Hot device (3) connection, the plasma-arc heater (3) include positive electrode (3-1), the first field coil (3-2), air inlet (3-3), electric arc (3-4), insulation lamination (3-5), the second field coil (3-6), negative electrode (3-7) and spout (3-8), plasma Positive electrode (3-1) and negative electrode (3-7) are provided with electro-arc heater (3), the first field coil is provided with positive electrode (3-1) (3-2), the second field coil (3-6) is provided with negative electrode (3-7), air inlet is provided with the middle part of plasma-arc heater (3) Mouth (3-3), air inlet (3-3) are internally provided with electric arc (3-4), and the end of air inlet (3-3) is communicated with spout (3-8).
- A kind of 2. small-sized wind tunnel stagnation point ablation experimental rig according to claim 1, it is characterised in that：The plasma The shell of electro-arc heater (3) is shielding sandwich type element.
- A kind of 3. small-sized wind tunnel stagnation point ablation experimental rig according to claim 1, it is characterised in that：The plasma Programmable controller (3-1) is installed, programmable controller (3-1) is heated with plasma-arc on the outside of electro-arc heater (3) Device (3) control connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721071367.8U CN207351650U (en) | 2017-08-23 | 2017-08-23 | A kind of small-sized wind tunnel stagnation point ablation experimental rig |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721071367.8U CN207351650U (en) | 2017-08-23 | 2017-08-23 | A kind of small-sized wind tunnel stagnation point ablation experimental rig |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207351650U true CN207351650U (en) | 2018-05-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721071367.8U Active CN207351650U (en) | 2017-08-23 | 2017-08-23 | A kind of small-sized wind tunnel stagnation point ablation experimental rig |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207351650U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108458852A (en) * | 2018-05-24 | 2018-08-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high-temperature tunnel quick changeable temperature potential device and alternating temperature voltage-transforming method |
-
2017
- 2017-08-23 CN CN201721071367.8U patent/CN207351650U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108458852A (en) * | 2018-05-24 | 2018-08-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high-temperature tunnel quick changeable temperature potential device and alternating temperature voltage-transforming method |
| 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 |
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| GR01 | Patent grant | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20240812 Granted publication date: 20180511 |
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| PP01 | Preservation of patent right |