CN201673029U - Sealing structure of spray pipe assembly for aerospace wind tunnel test device - Google Patents
Sealing structure of spray pipe assembly for aerospace wind tunnel test device Download PDFInfo
- Publication number
- CN201673029U CN201673029U CN2010201807890U CN201020180789U CN201673029U CN 201673029 U CN201673029 U CN 201673029U CN 2010201807890 U CN2010201807890 U CN 2010201807890U CN 201020180789 U CN201020180789 U CN 201020180789U CN 201673029 U CN201673029 U CN 201673029U
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- China
- Prior art keywords
- tunnel test
- wind tunnel
- spray pipe
- jet pipe
- test device
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- 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.)
- Expired - Fee Related
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Abstract
The utility model discloses a sealing structure of a spray pipe assembly for an aerospace wind tunnel test device, which comprises a plurality of spray pipes in sequential connection. The inner surfaces of the spray pipes are parabola-shaped. Flanges are connected among the spray pipes. One end of each spray pipe is provided with an O-shaped ring mounting groove. Due to the adoption of the above technical scheme, the plurality of spray pipes are sequentially connected. The construction is convenient and the use is reliable, and the disadvantages of air vent, slag inclusion, crack and the like in the casting steel are overcome. The inner hole of each spray pipe is parabola-shaped, thereby ensuring the high-speed parallel wind.
Description
Technical field
The utility model relates to the hermetically-sealed construction of a kind of Aero-Space wind tunnel test equipment with spout.
Background technology
Wind-tunnel is a basic equipment that carries out the aerodynamics experiment.Most of aerodynamic force experiment is up to now all finished in wind-tunnel.Because the complicacy of gas flow phenomenon and object (aircraft) geometric shape, many problems in aerodynamic studies and the aircraft pneumatic design all can not rely on theory or numerical simulation to solve merely, and must be by a large amount of experiments, find out its rule or data are provided, and combine research with theoretical the analysis, so just can deal with problems, because wind-tunnel is the basic equipment that carries out the aerodynamic force experiment, so the development of aeronautical technology is just directly relevant with the wind-tunnel development.Before any one aircraft formally designs, finalizes the design, all must be through a large amount of blowing experiments.
Spout is a critical component in the wind-tunnel.Existing spout adopts integral solder, occurs shortcomings such as pore, slag inclusion, crackle easily.
The utility model content
Technical problem to be solved in the utility model provides the hermetically-sealed construction of a kind of Aero-Space wind tunnel test equipment with spout., easy construction is used reliably, has eliminated shortcomings such as the pore in the steel-casting, slag inclusion, crackle.
For solving the problems of the technologies described above, the utility model adopts following technical scheme: the Aero-Space wind tunnel test equipment hermetically-sealed construction of spout, comprise the some jet pipes that connect successively, the inside surface of described jet pipe is a para-curve, for flange connects, described jet pipe one end is provided with O type circle mounting groove between the described jet pipe.
Described jet pipe is a steel-casting.
The utility model is owing to adopted technique scheme, and some jet pipes connect successively, and easy construction is used reliably, has eliminated shortcomings such as the pore in the steel-casting, slag inclusion, crackle.The jet pipe endoporus is a para-curve, has guaranteed high speed parallel wind.
Description of drawings
Fig. 1 is the structural representation of the utility model Aero-Space wind tunnel test equipment with the hermetically-sealed construction of spout.
Fig. 2 is the partial enlarged drawing at A place among Fig. 1.
Embodiment
Below in conjunction with accompanying drawing embodiment of the present utility model is further described.
Figure 1 shows that the hermetically-sealed construction of the utility model Aero-Space wind tunnel test equipment with spout, comprise the some jet pipes 1 that connect successively, the inside surface 11 of described jet pipe 1 is a para-curve, connect for flange between the described jet pipe 1, as shown in Figure 2, described jet pipe 1 one ends are provided with O type circle mounting groove 12.Described jet pipe 1 is a steel-casting.The utility model adopts some jet pipes to connect successively, and easy construction is used reliably, has eliminated shortcomings such as the pore in the steel-casting, slag inclusion, crackle.The jet pipe endoporus is a para-curve, has guaranteed high speed parallel wind.
Claims (2)
1. the hermetically-sealed construction with spout is equipped in the Aero-Space wind tunnel test, it is characterized in that: comprise the some jet pipes (1) that connect successively, the inside surface (11) of described jet pipe (1) is a para-curve, for flange connects, described jet pipe (1) one end is provided with O type circle mounting groove (12) between the described jet pipe (1).
2. according to the hermetically-sealed construction of the described Aero-Space wind tunnel test equipment of claim 1 with spout, it is characterized in that: described jet pipe (1) is a steel-casting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201807890U CN201673029U (en) | 2010-04-30 | 2010-04-30 | Sealing structure of spray pipe assembly for aerospace wind tunnel test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201807890U CN201673029U (en) | 2010-04-30 | 2010-04-30 | Sealing structure of spray pipe assembly for aerospace wind tunnel test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201673029U true CN201673029U (en) | 2010-12-15 |
Family
ID=43330441
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201807890U Expired - Fee Related CN201673029U (en) | 2010-04-30 | 2010-04-30 | Sealing structure of spray pipe assembly for aerospace wind tunnel test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201673029U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105716827A (en) * | 2014-12-03 | 2016-06-29 | 中航通飞研究院有限公司 | Amphibious aircraft blown flap wind tunnel test model |
| CN108195551A (en) * | 2018-01-18 | 2018-06-22 | 倪惠芳 | A kind of sealing structure for aerospace wind tunnel test nozzle component |
-
2010
- 2010-04-30 CN CN2010201807890U patent/CN201673029U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105716827A (en) * | 2014-12-03 | 2016-06-29 | 中航通飞研究院有限公司 | Amphibious aircraft blown flap wind tunnel test model |
| CN105716827B (en) * | 2014-12-03 | 2018-04-24 | 中航通飞研究院有限公司 | Amphibious aircraft blown flap model in wind tunnel |
| CN108195551A (en) * | 2018-01-18 | 2018-06-22 | 倪惠芳 | A kind of sealing structure for aerospace wind tunnel test nozzle component |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101215 Termination date: 20130430 |