CN111337218A - Mars wind tunnel with sand simulation function - Google Patents
Mars wind tunnel with sand simulation function Download PDFInfo
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- CN111337218A CN111337218A CN202010283837.7A CN202010283837A CN111337218A CN 111337218 A CN111337218 A CN 111337218A CN 202010283837 A CN202010283837 A CN 202010283837A CN 111337218 A CN111337218 A CN 111337218A
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- 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
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention aims to provide a Mars wind tunnel with sand dust simulation, which is horizontally arranged in a vacuum container and comprises a collector, a stable section, a contraction section, a test section, an ejector section, an outlet diffusion section, an ejector and a first diffusion section, wherein the test section is connected with the first diffusion section, the first diffusion section is connected with the ejector section, the ejector section is connected with the diffusion section, a transition equal-straight section is arranged between the ejector section and the diffusion section, the ejector is arranged at the inlet of the ejector section, the diffusion angle of the first diffusion section is not more than 5 degrees, and the inlet section area of the ejector section is larger than the outlet section area of the test section. The simulation of the wind speed of 5-100m/s in a large span range can be realized under the pressure of 100Pa by only consuming less air, the flow field of the test section is uniform and stable, and the sand dust environment of mars can be simulated under the low pressure.
Description
Technical Field
The invention relates to a Mars wind tunnel with sand and dust simulation.
Background
Wind tunnels are commonly used to study the aerodynamic performance of aircraft and their associated design, conventional wind tunnels being developed for aircraft designed to fly in the surface atmosphere. The Mars wind tunnel is a test simulation device developed aiming at the Mars atmospheric flight environment, and is different from a conventional wind tunnel, and the Mars wind tunnel can simulate gas components, atmospheric pressure, density, flow field environment and the like on the surface of a Mars. The mars are very thin in atmosphere, the main component of the atmosphere is carbon dioxide, the atmospheric density is about 1% of the earth (similar to the density at a height of 30-40km above the earth surface), the average pressure on the mars surface is only 600Pa, and local or regional sand storms on the mars can frequently occur in different seasons and different places of the mars. Because the atmospheric environment on the surface of the mars and the surface of the earth are greatly different, the conventional atmospheric environment wind tunnel cannot meet the requirement of further simulating the mars atmospheric environment. The conventional direct-current wind tunnel usually adopts a motor or an ejector as a driving source, when the motor is adopted as driving, the wind speed required by a spark simulation test cannot be formed in a low-pressure environment, and when the common ejector is adopted as driving, the influence of a saturated blocking phenomenon easily formed at an outlet by ejected airflow cannot be realized, and the high-wind-speed simulation in the low-pressure environment cannot be realized. In addition, the sand-dust simulation in the conventional mode is difficult to keep high consistency with the wind speed in a low-pressure environment, and the uniformity of the sand-dust distribution in the test section is difficult to ensure. Therefore, in order to meet the needs of experimental research related to the Mars environment in deep space exploration, it is necessary to develop research work of Mars wind tunnel, and a Mars wind tunnel capable of simulating the sand and dust environment of Mars is needed.
Disclosure of Invention
Based on the defects, the invention aims to provide the Mars wind tunnel with the sand dust simulation function, the wind tunnel is horizontally arranged in a low-pressure vacuum container, the wind tunnel can realize the simulation of the wind speed of 5-100m/s in a large-span range under the pressure of 100Pa by consuming less air quantity, the flow field of a test section is uniform and stable, and the sand dust environment of the Mars can be simulated under the low pressure.
In order to realize the purpose, the invention adopts the following technical scheme to realize the purpose: the utility model provides a take mars wind-tunnel of sand and dust simulation, this wind-tunnel level is placed in vacuum vessel, adopts the structure of straight-flow wind-tunnel, including collector, stable section, shrink section, experimental section, ejector section, export diffuser section and ejector, the collector is connected with stable section, stable section is connected with shrink section, shrink section and experimental section are connected, this wind-tunnel still includes first diffuser section, experimental section is connected with first diffuser section, first diffuser section is connected with the ejector section, the ejector section is connected with the diffuser section, be the equal straight section of one section transition between ejector section and the diffuser section, the entry of ejector section install the ejector, first diffuser section with certain angle diffusion, the diffusion angle is no longer than 5 °, the entry cross sectional area of ejector section be greater than the export cross sectional area of experimental section, the area ratio is more than 3 times. The first diffusion section is arranged at the test section and the ejector section, so that the ejector section and the test section form a high cross-sectional area ratio, the ejector efficiency is improved, the problem that the air speed cannot be further improved due to the fact that the low air pressure causes the air flow of the ejector to form blockage is avoided, and the upper limit of the air speed of the wind tunnel is further improved.
The invention also has the following technical characteristics:
1. the inside of the contraction section is detachably connected with a sand-dust nozzle, the height of the sand-dust nozzle is coincided with the central line of the wind tunnel, the sand-dust nozzle is arranged in the reverse airflow direction, and the sand-dust nozzle is far away from the inlet of the test section.
2. The cross-sectional area of the outlet of the test section is larger than that of the inlet, the inlet of the test section is square, the upper wall and the lower wall of the test section diffuse at a certain angle along the airflow direction, the outlet of the test section is rectangular, the width of the outlet of the test section is the same as that of the inlet of the test section, and the height of the outlet of the test section is larger than that of the inlet of the test section. The upper wall surface and the lower wall surface of the test section are changed to be provided with certain diffusion angles, so that the outlet area of the test section is larger than the inlet area, and the boundary layer blocking effect of the wind tunnel test section can be obviously improved.
3. The ejector comprises an ejector cavity shell, a plurality of ejector spray pipes and an ejector connecting air pipe, wherein the ejector cavity shell surrounds the outer wall of the ejector section by a circle and is in sealing connection with the outer wall of the ejector section to form a closed ejector cavity, the ejector spray pipes are located in the ejector cavity and mutually parallel to each other and radially penetrate through the ejector section at certain intervals, the head and the tail of each spray pipe are respectively communicated with the ejector cavity, the part of each ejector spray pipe, which is located in the ejector section, is provided with a plurality of horn-shaped small holes, and the small holes are symmetrically arranged in a square matrix.
4. One side of the test section is provided with a test section gate, an observation window is arranged on the test section gate, a mechanical hand wheel is arranged on the test section gate, the top of the test section is also provided with the observation window, and a pitot tube for measuring the wind speed and a dust concentration meter for measuring the sand concentration are detachably arranged on the upper wall of the test section. The pitot tube can simultaneously measure wind speed and gas pressure of a test section, a gate arranged on one side of the test section can be quickly opened and closed through a mechanical hand wheel, and a support and balance force measuring device is arranged on the wall of a wind tunnel hole on the other side surface of the test section, so that a test piece can be clamped and measured during testing. In addition, the whole test process can be observed or related tests such as PIV (particle image velocimetry) can be carried out through the top of the test section and the observation window on the gate of the test section.
The invention has the advantages and beneficial effects that: the wind tunnel is different from the traditional direct-current wind tunnel, does not adopt motor drive, adopts ejector drive, and can ensure that the consumed gas flow is less while the test section forms a large-span test wind speed under extremely low environmental air pressure. Book (I)The wind tunnel is horizontally placed in a low-pressure vacuum container, the pressure in the container is regulated to simulate the air pressure environment within the range of 100 plus 1500Pa, the simulation of the large-span wind speed range of 5-100m/s can be realized in the air pressure environment, the wind speed can be continuously regulated, the sand dust simulation of the sand dust particle size of 1-100 mu m under a certain wind speed in the low-pressure environment can be realized by arranging a sand dust injection device in a contraction section, and the concentration range can reach 0.1-1g/m3And the concentration can be continuously adjusted, and the test gas medium of the Mars wind tunnel can be air or gaseous carbon dioxide. The structure form of the direct-flow wind tunnel is adopted, the sand dust injection is not easy to form backflow, the sand dust is injected in a reverse airflow mode, the sand dust in the test section is uniformly distributed, and the nozzle cannot interfere the flow field of the test section.
Drawings
FIG. 1 is a front view of a Mars wind tunnel with sand and dust simulation.
FIG. 2 is a left side view of a Mars wind tunnel with sand simulation.
Fig. 3 is a cross-sectional view a-a in fig. 2.
In the figure: 1. the device comprises a collector, 2, a stabilizing section, 3, a contraction section, 4, a test section, 5, a first diffusion section, 6, an ejector section, 6-1, an equal straight section, 7, an outlet diffusion section, 8, an ejector, 8-1, an ejector cavity shell, 8-2, an ejector cavity, 9, an ejector spray pipe, 10, an ejector connecting gas pipe, 11, a sand dust nozzle, 12, a sand dust conveying pipeline, 13, a connecting bolt, 14, an outlet diffusion section flange, 15, a test section gate, 16, an observation window, 17, a connecting flange, 18 and a mechanical hand wheel.
Detailed Description
The invention will be further illustrated by way of example with reference to the accompanying drawings.
Example 1
A mars wind tunnel with sand and dust simulation is horizontally placed in a low-pressure vacuum container and adopts a direct-flow wind tunnel structure form, and comprises a collector 1, a stable section 2, a contraction section 3, a test section 4, an ejector section 6, an outlet diffusion section 7 and an ejector 8, wherein the collector 1 is in a horn mouth shape, the collector 1 is connected with an inlet of the stable section 2, the cross section of the stable section 2 is square, a connecting port of a layer of honeycomb device and a plurality of layers of damping nets is reserved in the stable section 2, the honeycomb device and the damping nets are optional parts and can be selectively installed according to test requirements, an outlet of the stable section 2 is connected with an inlet of the contraction section 3 through a flange, an outlet of the contraction section 3 is connected with an inlet of the test section 4 through a flange, the wind tunnel further comprises a first diffusion section 5, an outlet of the test section 4 is connected with an inlet of the first diffusion section 5 through a flange, an outlet of the first diffusion section 5 is connected with an inlet of the ejector section 6 through, the outlet of the ejector section 6 is connected with the inlet of the diffusion section 7 through a flange, an equal-straight section 6-1 of one section of transition is arranged between the ejector section 6 and the outlet diffusion section, the inlet of the ejector section 6 is provided with the ejector, the first diffusion section 5 diffuses at a certain angle, the diffusion angle is not more than 5 degrees, the inlet section area of the ejector section 6 is larger than the outlet section area of the test section 4, and the area ratio is more than 3 times. During testing, the wind tunnel is positioned in a vacuum container, the vacuum container can provide air pressure (100 + 1500Pa) required by the testing for the Mars wind tunnel, gas required by the testing enters the ejector cavity 8-1 through the ejector connecting air pipe 10 and is rapidly ejected through the small holes in the ejector spray pipe 9, the gas forms suction in a rapid expansion mode, and airflow outside the wind tunnel can be sucked from the wind tunnel inlet and is discharged from the outlet diffusion section after passing through the testing section.
The inside of contraction section 3 can dismantle and be connected with sand and dust nozzle 11, sand and dust nozzle 11 highly coincide with the wind-tunnel central line, adopt the counter-current direction to arrange, sand and dust nozzle keep away from the entry of test section 4, sand and dust nozzle 11 can reverse installation, also can forward installation.
One side of the test section 4 is provided with a test section gate 15, the test section gate 15 is provided with an observation window 16 and a mechanical hand wheel 18, a wind tunnel hole wall on the other side of the test section 4 is provided with a support and balance force measuring device, the top of the test section 4 is also provided with the observation window 16, and a pitot tube for measuring wind speed and a dust concentration meter for measuring sand concentration are detachably arranged on the upper wall of the test section 4.
The sectional area of the outlet of the test section is larger than that of the inlet of the test section, the inlet of the test section is square and is diffused at a slight angle along the upper wall and the lower wall of the test section in the airflow direction, and the outlet of the test section is rectangular, the width of the outlet of the test section is the same as that of the inlet of the test section, but the height of the outlet of the test section is larger than that of the inlet of the test section.
The ejector 8 comprises an ejector cavity shell 8-, a plurality of ejector spray pipes 9 and an ejector connecting air pipe 10, the ejector cavity shell 8-1 surrounds a circle of the outer wall of the ejector section 6 and is in sealing connection with the outer wall of the ejector section to form a closed ejector cavity 8-2, the ejector spray pipes 9 are located in the ejector cavity 8 and mutually parallel to radially penetrate through the ejector section 6 at certain intervals, the head and the tail of each spray pipe 9 are respectively communicated with the ejector cavity 8-2, the ejector cavity 8 is communicated with the ejector connecting air pipe 10, a plurality of horn-shaped small holes with narrow throat diameters are formed in the part, located in the ejector section 6, of each ejector spray pipe 9, and the small holes are symmetrically arranged in a square array.
Example 2
The structure of embodiment 1 is adopted to this embodiment, and the air feed flow who enters into ejector cavity 8 is adjusted through high accuracy governing valve, changes the jet flow of ejector, and then changes the wind speed size in the experimental section, and 9 ejector spray pipes 9 are equidistant parallel arrangement, and it has 9 injection apertures to open on every spray pipe, totally 81 apertures.
Example 3
The structure of embodiment 1 is adopted in this embodiment, when carrying out the sand and dust simulation test, adopt the mode of forced draught conveying sand and dust, make the test gas of higher pressure get into sand and dust pipeline 12 and mix with sand and dust and carry, through the venturi sprayer, finally spray from the sand and dust nozzle 11 of shrink section, in order to make the sand and dust in test section 4 spread evenly, the exit structure that sand and dust nozzle 11 spouts adopts the crisscross form of multilayer, adopt the jet direction of contrary air current, this kind of mode can also make the nozzle keep away from the test section entry, improve the flow field quality of test section. When the sand-dust test simulation is not needed, the sand-dust nozzle and the pipeline thereof can be disassembled, and the dust concentration meter is disassembled, so that the flow field quality of the test section is further improved. When the sand blowing test is carried out by adopting the reverse airflow mode, the wind speed of the test section 4 is required to meet the requirement of more than 32.5m/s, and when the wind speed is lower than 32.5m/s and sand blowing is still required, the mode of installing the sand-dust nozzle 11 in the forward direction can be adopted.
Example 4
The structure of embodiment 1 is adopted to this embodiment, in order to make experimental section 4 can reach the wind speed more than 100m/s under extremely low atmospheric pressure, between ejector section 6 and experimental section 4, connect through first diffuser section 5, the diffusion angle of first diffuser section 5 is about 4.6, and the entry of ejector section 6 reaches 4 times with the exit area ratio of experimental section 4, can obviously improve ejector efficiency, avoids the problem that the low atmospheric pressure leads to the air current of ejector to form the jam and the wind speed that leads to can't further improve. The airflow ejected by the ejector of the ejector section 6 is mixed with the airflow discharged by the test section 4 and then discharged through the outlet diffusion section 7, and the diffusion angle of the outlet diffusion section 7 is 5 degrees.
Example 5
In this embodiment, the structure of example 1 is adopted, the contraction ratio of the wind tunnel (the ratio of the cross-sectional area of the outlet of the stabilizing section 2 to the cross-sectional area of the inlet of the test section 4) is selected to be 12, and the higher contraction ratio can reduce the longitudinal turbulence influence of the test section 4. According to the test requirement, the honeycomb device and the damping net reserved in the stabilizing section 2 are selected and installed, so that the turbulence degree of the test section 4 can be further reduced.
The inlet section of the test section 4 is 210mm wide, × mm high and 210mm high, the upper wall surface and the lower wall surface have a diffusion angle of 0.5 degree, the outlet section of the test section 4 is 210mm wide, × mm high and 218mm high, the increase of the outlet section area of the test section 4 can improve the boundary layer blocking effect of the wind tunnel test section 4.
Claims (5)
1. The utility model provides a take mars wind-tunnel of sand and dust simulation, this wind-tunnel level is placed in vacuum vessel, adopts the structure of straight-flow wind-tunnel, including collector (1), stable section (2), shrink section (3), experimental section (4), ejector section (6), export diffuser (7) and ejector (8), collector (1) are connected with stable section (2), and stable section (2) are connected with shrink section 3, and shrink section (3) are connected with experimental section (4), its characterized in that: still include first diffuser section (5), experimental section (4) are connected with first diffuser section (5), and first diffuser section (5) are connected with ejector section (6), and ejector section (6) are connected with diffuser section (7), are equal straight section (6-1) of one section transition between ejector section (6) and diffuser section (7), the entry of ejector section (6) install the ejector, first diffuser section (5) with certain angle diffusion, the diffusion angle is no longer than 5, the entry cross sectional area of ejector section (6) be greater than the export cross sectional area of experimental section (4), the area ratio is more than 3 times.
2. A Mars wind tunnel with sand and dust simulation according to claim 1, characterized in that: the inside of contraction section (3) can be dismantled and be connected with sand and dust nozzle (11), sand and dust nozzle (11) highly coincide with the wind-tunnel central line, adopt the counter-current direction to arrange, sand and dust nozzle keep away from the entry of test section (4).
3. A sand and dust simulated mars wind tunnel according to claim 1 or 2, wherein: the sectional area of the outlet of the test section (4) is larger than that of the inlet, the inlet of the test section (4) is square, the upper wall and the lower wall of the test section (4) diffuse at a certain angle along the airflow direction, the outlet of the test section (4) is rectangular, the width of the outlet of the test section is the same as that of the inlet of the test section (4), and the height of the outlet of the test section is larger than that of the inlet of the test section (4).
4. A sand and dust simulated mars wind tunnel according to claim 1 or 2, wherein: the ejector (8) comprises an ejector cavity shell (8-1), a plurality of ejector nozzles (9) and an ejector connecting air pipe (10), the ejector chamber shell (8-1) surrounds the outer wall of the ejector section (6) for a circle, and is hermetically connected with the outer wall of the ejector section to form a closed ejector cavity (8-2), a plurality of ejector nozzles (9) are positioned in the ejector cavity (8) and are parallel to each other and radially penetrate through the ejector section (6) at certain intervals, the head and the tail of each nozzle (9) are respectively communicated with the ejector cavity (8-2), the ejector cavity (8) is communicated with an ejector connecting air pipe (10), the ejector nozzle (9) is provided with a plurality of horn-shaped small holes in the ejector section (6), and the small holes are symmetrically arranged in a square matrix.
5. A sand and dust simulated mars wind tunnel according to claim 1 or 2, wherein: one side of the test section (4) is provided with a test section gate (15), the test section gate (15) is provided with an observation window (16) and is provided with a mechanical hand wheel (18), a wind tunnel hole wall on the other side of the test section (4) is provided with a support and a balance force measuring device, the top of the test section (4) is also provided with the observation window (16), and a pitot tube for measuring wind speed and a dust concentration meter for measuring sand concentration are detachably arranged on the upper wall of the test section (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202010283837.7A CN111337218A (en) | 2020-04-13 | 2020-04-13 | Mars wind tunnel with sand simulation function |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010283837.7A CN111337218A (en) | 2020-04-13 | 2020-04-13 | Mars wind tunnel with sand simulation function |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111649953A (en) * | 2020-07-23 | 2020-09-11 | 中国航发湖南动力机械研究所 | Sand dust deposition test device |
| CN111678707A (en) * | 2020-07-23 | 2020-09-18 | 中国航发湖南动力机械研究所 | Dust deposition characteristic test system |
| CN112577699A (en) * | 2020-12-30 | 2021-03-30 | 北京航天益森风洞工程技术有限公司 | Testing device |
| CN112649173A (en) * | 2020-12-30 | 2021-04-13 | 哈尔滨工业大学 | Return flow type wind tunnel device for simulating low-pressure low-density dust storm environment of mars |
| CN112761898A (en) * | 2021-01-20 | 2021-05-07 | 沈观清 | Front-mounted wind speed pipe arranged at front part of wind driven generator |
| CN113252290A (en) * | 2021-04-22 | 2021-08-13 | 哈尔滨工业大学 | Mars low-pressure supersonic ejector with ultralow-pressure input and high-wind-speed output |
| CN113390603A (en) * | 2021-06-17 | 2021-09-14 | 哈尔滨工业大学 | Wind speed measuring device for low-pressure high-speed Mars wind tunnel and precision improving method thereof |
| CN113390600A (en) * | 2021-07-26 | 2021-09-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Shock tunnel test simulation device and method for pneumatic thermal effect of pyrolysis gas |
| CN113804393A (en) * | 2021-09-07 | 2021-12-17 | 哈尔滨工业大学 | Sample supporting mechanism with balance for Mars low-pressure wind tunnel |
| CN114061888A (en) * | 2020-08-03 | 2022-02-18 | 中国科学院西北生态环境资源研究院 | Wind tunnel system for low-temperature and low-pressure wind-sand environment |
| CN114802833A (en) * | 2022-05-17 | 2022-07-29 | 哈尔滨工业大学 | Simulation device for simulating environmental effects of Mars surface rotational flow and dust storm |
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2020
- 2020-04-13 CN CN202010283837.7A patent/CN111337218A/en active Pending
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111678707A (en) * | 2020-07-23 | 2020-09-18 | 中国航发湖南动力机械研究所 | Dust deposition characteristic test system |
| CN111649953A (en) * | 2020-07-23 | 2020-09-11 | 中国航发湖南动力机械研究所 | Sand dust deposition test device |
| CN114061888A (en) * | 2020-08-03 | 2022-02-18 | 中国科学院西北生态环境资源研究院 | Wind tunnel system for low-temperature and low-pressure wind-sand environment |
| CN114061888B (en) * | 2020-08-03 | 2024-03-01 | 中国科学院西北生态环境资源研究院 | Low-temperature low-pressure wind sand environment wind tunnel system |
| CN112649173A (en) * | 2020-12-30 | 2021-04-13 | 哈尔滨工业大学 | Return flow type wind tunnel device for simulating low-pressure low-density dust storm environment of mars |
| CN112649173B (en) * | 2020-12-30 | 2023-08-11 | 哈尔滨工业大学 | Reflux type wind tunnel device for simulating Mars low-pressure low-density dust storm environment |
| CN112577699A (en) * | 2020-12-30 | 2021-03-30 | 北京航天益森风洞工程技术有限公司 | Testing device |
| CN112761898A (en) * | 2021-01-20 | 2021-05-07 | 沈观清 | Front-mounted wind speed pipe arranged at front part of wind driven generator |
| CN113252290A (en) * | 2021-04-22 | 2021-08-13 | 哈尔滨工业大学 | Mars low-pressure supersonic ejector with ultralow-pressure input and high-wind-speed output |
| CN113390603A (en) * | 2021-06-17 | 2021-09-14 | 哈尔滨工业大学 | Wind speed measuring device for low-pressure high-speed Mars wind tunnel and precision improving method thereof |
| 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 |
| CN113390600A (en) * | 2021-07-26 | 2021-09-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Shock tunnel test simulation device and method for pneumatic thermal effect of pyrolysis gas |
| CN113804393A (en) * | 2021-09-07 | 2021-12-17 | 哈尔滨工业大学 | Sample supporting mechanism with balance for Mars low-pressure wind tunnel |
| CN114802833A (en) * | 2022-05-17 | 2022-07-29 | 哈尔滨工业大学 | Simulation device for simulating environmental effects of Mars surface rotational flow and dust storm |
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