CN112649173B - Reflux type wind tunnel device for simulating Mars low-pressure low-density dust storm environment - Google Patents
Reflux type wind tunnel device for simulating Mars low-pressure low-density dust storm environment Download PDFInfo
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- CN112649173B CN112649173B CN202011629687.7A CN202011629687A CN112649173B CN 112649173 B CN112649173 B CN 112649173B CN 202011629687 A CN202011629687 A CN 202011629687A CN 112649173 B CN112649173 B CN 112649173B
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- G—PHYSICS
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
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Abstract
The application provides a reflux type wind tunnel device for simulating a Mars low-pressure low-density dust storm environment, which comprises a reflux type wind tunnel, an ejector and an ejector, wherein the reflux type wind tunnel comprises a stabilizing section, a contracting section, a test section, a first diffusion section, a second diffusion section, a mixing section, a third diffusion section and a large-angle diffusion section which are sequentially communicated, a first corner is communicated between the first diffusion section and the second diffusion section, a second corner is communicated between the second diffusion section and the mixing section, a third corner and a fourth corner are sequentially communicated between the third diffusion section and the large-angle diffusion section, a corner guide vane is arranged in each corner, the ejector is arranged in the mixing section, and the ejector is arranged in the contracting section. According to the application, the ejector is combined with the backflow type wind tunnel, the small inlet pressure of the ejector can reach the wind speed required by the test section, the air flow quality is improved, the loss is reduced, the overall size of the wind tunnel is reduced, and the vacuumizing cost is reduced by adopting a mode of combining a large shrinkage ratio with a large-angle diffusion section.
Description
Technical Field
The application belongs to the field of ground simulation of deep space exploration space environments, and particularly relates to a reflux type wind tunnel device for simulating a Mars low-pressure low-density dust storm environment.
Background
The Mars wind tunnel is a simulation device developed for the environment of Mars extreme, the space of China is launched, but for the Mars vehicle of space, the wind and heat simulation of low wind speed can be carried out only by using the prior art, for the environment of Mars, the most obvious is the environment of low pressure, high wind speed and sand dust, so that a wind tunnel capable of simulating the environment of Mars low pressure, high wind speed and sand dust is necessarily designed, because the size of the Mars vehicle is large, the required test section is large, and for the linear wind tunnel, a large vacuum cabin is required outside to finish wind speed formation, because the wind tunnel is too large in size, the vacuum cabin is too large in size, in order to generate a low pressure environment, a vacuum pump set is required to vacuumize, the vacuum cabin with too large size consumes a large amount of time and is economical, and for the reflux wind tunnel, the vacuum cabin is not required to be used, the wind speed cost can be generated by self, the volume is small, and the vacuumization cost is low. For wind speed simulation, a fan or an ejector is usually adopted, but the fan is difficult to achieve high wind speed under a low-pressure environment, and for a linear ejector type wind tunnel, although the high wind speed can be achieved, the ejector is utilized to jet high-pressure gas, so that ambient pressure is reduced, because the pressure of a test section is high, the wind speed is formed due to pressure difference, but the gas mass flow passing through the test section is only the mass flow of ejected gas, and the gas coming out of the ejector is directly extracted, so that the efficiency is low, too much gas is consumed to achieve high wind speed, the efficiency is necessarily improved, and for a backflow type wind tunnel, the mass flow passing through the test section is the sum of the two, so that the efficiency is high, and waste of resources is not caused, so that a spark wind tunnel capable of simulating a sand dust environment is needed.
Disclosure of Invention
In view of the above, the application aims to provide a reflux type wind tunnel device simulating a Mars low-pressure low-density dust storm environment, which uses an ejector to drive and reflux type wind tunnels in a combined mode, the inlet pressure of the small ejector can reach the wind speed required by a test section, and the mode of combining a large shrinkage ratio with a large-angle diffusion section is adopted, so that the air flow quality is improved, the loss is reduced, the overall size of the wind tunnel is reduced, and the vacuumizing cost is reduced.
In order to achieve the above purpose, the technical scheme of the application is realized as follows:
the utility model provides a simulation spark low pressure low density dust storm environment's backward flow type wind tunnel device, includes backward flow type wind tunnel, ejector and sprayer, backward flow type wind tunnel including the stable section, shrink section, test section, first diffusion section, second diffusion section, mixed section, third diffusion section and the big angle diffusion section of intercommunication in proper order, the intercommunication has first turning between first diffusion section and second diffusion section, the intercommunication has the second turning between second diffusion section and mixed section, the intercommunication has third turning and fourth turning in proper order between third diffusion section and the big angle diffusion section, all be equipped with a turning guide vane in every turning, the ejector set up in mixed section, the sprayer set up in shrink section, the entry cross-section area of big angle diffusion section is less than the export cross-section area, the diffusion angle of big angle diffusion section is 15, shrink section's shrink ratio be 12, the diffusion angle of first diffusion section, second diffusion section and third diffusion section is 6-8.
Further, the third diffuser is arranged opposite to the large-angle diffuser and the stabilizing section, and the third corner and the fourth corner are symmetrically arranged.
Further, an anti-separation net is arranged in the large-angle diffusion section.
Further, a honeycomb and a gauze are arranged in the stabilizing section, and the honeycomb is arranged close to the inlet of the stabilizing section.
Further, the stabilizing section is a constant cross-section pipeline, and the cross-section shape is square.
Further, the ejector comprises a pressure chamber and a plurality of ejection spray pipes, and a plurality of nozzles are uniformly arranged on each ejection spray pipe.
Further, the ejector is communicated with an air source system, the second diffusion section is communicated with a vacuum system, the vacuum system is communicated with a vacuum secondary buffer tank, and an air speed simulation system is arranged between the air source system and the ejector.
Furthermore, the ejector is communicated with the sand and dust system through the gas pipe, the sand and dust system is supplied by the gas source system, the height of the ejector coincides with the central line of the wind tunnel, the ejector is arranged in a countercurrent direction, and the ejector is far away from the inlet of the test section.
Further, the outlet cross-sectional area of the test section is larger than the inlet cross-sectional area, and the four surfaces of the hole wall are respectively diffused by 0.50 degrees along the air flow direction.
Further, an observation window is mounted on the side wall of the test section.
Compared with the prior art, the reflux type wind tunnel device for simulating the Mars low-pressure low-density dust storm environment has the following advantages:
the pressure of the application is continuously adjustable between 100 Pa and 1500Pa, the wind speed is continuously adjustable between 0m/s and 180m/s, and the sand dust concentration is between 0.1 g/cm and 1g/cm 3 The spark backflow type wind tunnel capable of simulating the sand dust environment is continuously adjustable, the vacuumizing cost is greatly reduced, the injection efficiency of the injector is improved, and the economy is high.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic structural diagram of a reflux wind tunnel device simulating a Mars low-pressure low-density dust storm environment according to an embodiment of the application;
FIG. 2 is a schematic diagram of a combination of a reflux wind tunnel device and related systems for simulating a Mars low-pressure low-density dust storm environment according to an embodiment of the application;
FIG. 3 is a schematic structural view of an ejector nozzle on an ejector.
Reference numerals illustrate:
1-honeycomb device, 2-gauze, 3-stabilizing section, 4-contracting section, 5-testing section, 6-first diffusion section, 7-first corner, 8-first corner deflector, 9-second diffusion section, 10-second corner, 11-second corner deflector, 12-pressure chamber, 13-ejector, 14-mixing section, 15-third diffusion section, 16-third corner, 17-third corner deflector, 18-fourth corner deflector, 19-fourth corner, 20-large angle diffusion section, 21-separation preventing net, 22-ejector, 23-gas pipe, 24-ejector nozzle, 25-gas source system, 26-sand dust system, 27-vacuum system, 28-vacuum secondary buffer tank, 29-wind speed simulation system.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other.
The application will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1-3, a reflux wind tunnel device simulating a spark low pressure low density dust storm environment comprises a reflux wind tunnel, an ejector 13 and an ejector 22, wherein the reflux wind tunnel comprises a stabilizing section 3, a contracting section 4, a test section 5, a first diffusing section 6, a second diffusing section 9, a mixing section 14, a third diffusing section 15 and a large angle diffusing section 20 which are sequentially communicated, a first corner 7 is communicated between the first diffusing section 6 and the second diffusing section 9, a second corner 10 is communicated between the second diffusing section 9 and the mixing section 14, a third corner 16 and a fourth corner 19 are sequentially communicated between the third diffusing section 15 and the large angle diffusing section 20, a corner deflector is arranged in each corner, the ejector 13 is arranged in the mixing section 14, the ejector 22 is arranged in the contracting section 4, the inlet cross-sectional area of the large angle diffusing section 20 is smaller than the outlet cross-sectional area, the large angle diffusing section 20 is 15 °, the contracting section 4 is contracted by 12, and the contracting ratio of the first diffusing section 6, the second diffusing section 9 and the third diffusing section 15 are both.
The third diffuser 15 is arranged opposite to the high angle diffuser 20 and the stabilizer 3, and the third corner 16 and the fourth corner 19 are symmetrically arranged.
Inside the stabilizing section 3 there is a honeycomb 1 and a gauze 2, and the honeycomb 1 is arranged close to the inlet of the stabilizing section 3. The honeycomb device 1 has the functions of dividing the incoming flow of the stabilizing section, reducing the separation and divergence of the air flow and improving the air flow characteristic of the outlet of the stabilizing section. The effect of the screen 2 is to reduce the turbulence of the air flow, where the screen is very fine, dividing the larger vortices into smaller vortices to facilitate attenuation of the turbulence.
The ejector 13 comprises a pressure chamber 12 and nine ejector jet pipes 24, the nine ejector jet pipes 24 are arranged in parallel at equal intervals, and nine nozzles are uniformly arranged on each ejector jet pipe 24.
The ejector 14 is communicated with an air source system 25, the second diffusion section 9 is communicated with a vacuum system 27, the vacuum system 27 is communicated with a vacuum secondary buffer tank 28, and an air speed simulation system 29 is arranged between the air source system 25 and the ejector 14.
The ejector 22 is communicated with a sand and dust system 26 through a gas pipe 23, the sand and dust system 26 is supplied by a gas source system 25, the height of the ejector 22 coincides with the central line of the wind tunnel, and the ejector 22 is arranged in a countercurrent direction and is far away from the inlet of the test section. The wind sand mixture sprays sand dust to the inside of the wind tunnel through the gas pipe and the spray pipe, the sand dust is sprayed more uniformly in a reverse spraying mode, and the spray pipe adopts a Venturi sprayer.
For test section 5 we used a square profile with the following advantages:
(1) for the yaw test of Mars aircraft it is often required that the wind tunnel bedplate rotates with the model-balance system, and that the square cross-section bedplate is flat, which can meet this requirement.
(2) Because the bottom surface is the plane, the experimenter can load and unload the model with the air inlet.
(3) The side wall is flat, so that the installation of the observation window is convenient, and the observation experiment and the like are facilitated.
(4) Flat sidewalls can be used for half-model experiments.
In the closed test section, the thickness of the boundary layer of the wall surface along the flow direction is gradually increased, so that the section of the bit stream is gradually reduced, the flow speed is continuously increased, and a negative static pressure gradient (pressure is gradually reduced) is generated along the axial direction. This subjects the model to an additional drag, known as horizontal buoyancy, that is not experienced by an atmospheric flight, the cross-sectional area of the outlet through the test section 5 being greater than the cross-sectional area of the inlet and diffusing 0.50 ° along each side of the airflow direction wall to eliminate the horizontal buoyancy.
The diffuser section functions to convert the kinetic energy of the gas flow into pressure energy. Since wind tunnel loss is proportional to the flow velocity to the third power, the flow through the test section should be reduced in velocity as much as possible to convert kinetic energy into pressure energy. But deceleration is necessarily accompanied by a loss, i.e. the kinetic energy may not be entirely converted into pressure energy. According to the principle of minimum loss, the diffusion angle of the diffusion section is designed to be 6 degrees, and the section of the diffusion section is square.
The effect of the constriction 4 is to accelerate the air flow to the speed required for the experiment. The method is beneficial to improving the shrinkage ratio of the wind tunnel, and being capable of improving the uniformity of the air flow of the test section and reducing the turbulence. Therefore, a large contraction ratio is adopted, a large-angle diffusion section 20 is added in front of the stabilizing section in order to increase the contraction ratio without increasing the wind tunnel size, an anti-separation net 21 is arranged in the large-angle diffusion section 20 in order to prevent separation caused by a large diffusion angle, and the number of layers of the net is determined by the size of the diffusion angle.
The stabilizing section 3 is typically a constant cross-section pipe. Downstream is connected to the constriction 4, so that the size of the area depends on the requirements of the wind tunnel constriction ratio. If the cross-sectional shape of the stabilizing section 3 is similar to that of the test section, the constriction section can be made simpler. The stabilizing sections again take the form of squares.
The corner is an important component of the back-flow wind tunnel. The total loss of air flow at the four corners can account for 40-60% of the total loss of the wind tunnel. The air flow passing through the corners is easily separated and many eddies occur, thus making the flow uneven or pulsating. Corner baffles must therefore be provided at the corners in order to prevent separation and improve flow.
The ejector provides a power source for the wind speed of the test section of the spark dust cabin. The ejector is arranged at the mixing section and mainly comprises a pressure chamber and an ejector nozzle, the ejector nozzle is used for ejecting gas and ejected gas to be mixed at the mixing section, the pressure chamber is connected with a gas supply pipeline controlled by a valve, and the pressure chamber is used for providing stable pressure for the ejector nozzle and ensuring that the gas flow states of outlets of all nozzles are kept consistent.
The air source system 25, the sand dust system 26, the vacuum system 27, the vacuum secondary buffer tank 28 and the wind speed simulation system 29 are all existing systems, and are not described in detail.
As shown in fig. 2, which is a diagram of the wind tunnel system, the wind tunnel is firstly pumped down to be directly discharged into the atmosphere under the action of the vacuum system, and the vacuum secondary buffer tank 28 is also pumped down until the pressure drops to the specified pressure. The air supply valve of the air supply system 25 is opened, the air supply system 25 provides a stable pressure air flow to the air speed simulation system 29, the air reaches the spray pipe through the air pipe connected with the ejector 13, and is rapidly sprayed out through the ejector spray pipe 24, the air forms suction force in a rapid expansion mode, the air flow at other positions of the wind tunnel can be sucked together with the ejected air, the air passes through the test section 5, after the pressure reaches the designated pressure, the redundant air is discharged out of the vacuum secondary buffer tank 28 by the vacuum system 27, the air speed simulation system 29 is regulated, the air speed of the test section 5 reaches the predetermined air speed, the sand and dust system 26 starts to work, the air supply system 25 carries sand and dust with a certain concentration to spray into the wind tunnel, the spraying amount is regulated by the sand and dust system 26 until the designated sand and dust concentration is reached, the test is started, and after the test is finished, the systems are sequentially closed.
The ejector is optimized by adopting a mode of combining driving and backflow type wind tunnel by the ejector, so that when the ambient pressure is 1000Pa, the inlet pressure of the ejector only needs 70000Pa, the wind speed of a test section can exceed 180m/s, and the mode of combining large shrinkage ratio with a large-angle diffusion section is adopted, so that the air flow quality is improved, the loss is reduced, the overall size of the wind tunnel is reduced, and the vacuumizing cost is reduced.
The foregoing description of the preferred embodiments of the application is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the application.
Claims (8)
1. A reflux type wind tunnel device for simulating a Mars low-pressure low-density dust storm environment is characterized in that: the air conditioning system comprises a backflow type wind tunnel, an ejector (13) and an ejector (22), wherein the backflow type wind tunnel comprises a stabilizing section (3), a contracting section (4), a test section (5), a first diffusion section (6), a second diffusion section (9), a mixing section (14), a third diffusion section (15) and a large-angle diffusion section (20) which are sequentially communicated, a first corner (7) is communicated between the first diffusion section (6) and the second diffusion section (9), a second corner (10) is communicated between the second diffusion section (9) and the mixing section (14), a third corner (16) and a fourth corner (19) are sequentially communicated between the third diffusion section (15) and the large-angle diffusion section (20), a corner deflector is arranged in each corner, the ejector (13) is arranged in the mixing section (14), the ejector (22) is arranged in the contracting section (4), the cross-section area of the large-angle diffusion section (20) is smaller than the outlet cross-section, the large-angle diffusion section (20) is the inlet cross-section area of the contracting section (4), the large-angle diffusion section (20) is the contracting section (6), the air conditioning system (15) is communicated with the third corner (15) and the air supply system (15), the second diffusion section (9) is communicated with the vacuum system (27), the vacuum system (27) is communicated with the vacuum secondary buffer tank (28), a wind speed simulation system (29) is arranged between the air source system (25) and the ejector (13), the ejector (22) is communicated with the sand and dust system (26) through the air pipe (23), the sand and dust system (26) is supplied with air by the air source system (25), the height of the ejector (22) coincides with the central line of the wind tunnel, the air is distributed in a countercurrent direction, and the ejector (22) is far away from the inlet of the test section.
2. A back-flow wind tunnel device for simulating a low-pressure low-density dust storm environment as defined in claim 1 wherein: the third diffusion section (15) is arranged opposite to the large-angle diffusion section (20) and the stabilizing section (3), and the third corner (16) and the fourth corner (19) are symmetrically arranged.
3. A back-flow wind tunnel device for simulating a low-pressure low-density dust storm environment of a Mars according to claim 1 or 2, wherein: an anti-separation net (21) is arranged in the large-angle diffusion section (20).
4. A reflux type wind tunnel device for simulating a spark low pressure low density dust storm environment as claimed in claim 3, wherein: a honeycomb device (1) and a gauze (2) are arranged in the stabilizing section (3), and the honeycomb device (1) is arranged close to the inlet of the stabilizing section (3).
5. A back-flow wind tunnel device for simulating a low-pressure, low-density dust storm environment as claimed in claim 1, 2 or 4 wherein: the stabilizing section (3) is a constant-section pipeline, and the section shape of the stabilizing section is square.
6. The reflux type wind tunnel device for simulating a spark low-pressure low-density dust storm environment as set forth in claim 5, wherein: the ejector (13) comprises a pressure chamber (12) and a plurality of ejector nozzles (24), and each ejector nozzle (24) is uniformly provided with a plurality of nozzles.
7. A back-flow wind tunnel device for simulating a low-pressure low-density dust storm environment of a Mars according to claim 1 or 2, wherein: the outlet cross-sectional area of the test section (5) is larger than the inlet cross-sectional area, and the four surfaces of the hole wall are respectively diffused by 0.50 degrees along the air flow direction.
8. The reflux type wind tunnel device for simulating a spark low-pressure low-density dust storm environment as claimed in claim 7, wherein: an observation window is arranged on the side wall of the test section (5).
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| CN202011629687.7A CN112649173B (en) | 2020-12-30 | 2020-12-30 | Reflux type wind tunnel device for simulating Mars low-pressure low-density dust storm environment |
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| CN202011629687.7A CN112649173B (en) | 2020-12-30 | 2020-12-30 | Reflux type wind tunnel device for simulating Mars low-pressure low-density dust storm environment |
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| CN112649173B true CN112649173B (en) | 2023-08-11 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113049210B (en) * | 2021-06-01 | 2021-08-27 | 中国航空工业集团公司沈阳空气动力研究所 | Measuring system for air flow energy mixing |
| CN113390603B (en) * | 2021-06-17 | 2022-09-13 | 哈尔滨工业大学 | Wind speed measuring device for low-pressure high-speed Mars wind tunnel and precision improving method thereof |
| CN114789802A (en) * | 2022-06-01 | 2022-07-26 | 哈尔滨工业大学 | Porous injection device for generating multi-type Mars rotational flows |
| CN115290287B (en) * | 2022-10-08 | 2022-12-09 | 中国空气动力研究与发展中心低速空气动力研究所 | High-altitude low-density wind tunnel test system and method and wind speed measurement method |
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