CN212674404U - Mini experience device of wind tunnel dynamic test airplane model - Google Patents
Mini experience device of wind tunnel dynamic test airplane model Download PDFInfo
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- CN212674404U CN212674404U CN202021966672.5U CN202021966672U CN212674404U CN 212674404 U CN212674404 U CN 212674404U CN 202021966672 U CN202021966672 U CN 202021966672U CN 212674404 U CN212674404 U CN 212674404U
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Abstract
The utility model discloses a mini device of experiencing of wind-tunnel dynamic test aircraft model relates to the wind-tunnel test field, including base and fixed plate, the top fixed mounting of base has the fan, the top of base and the one side fixed mounting that is located the fan have control panel, fixedly connected with fixed plate between control panel and the fan, the utility model discloses beneficial increase: be provided with control panel and experimental aircraft, realized through controlling the platform, control experimental aircraft model, can observe the state of air current on aircraft model surface, be provided with the wind-tunnel test cabin of taking light and atomising head, the state of air flow through experimental aircraft model can all be observed no matter daytime night, can carry out fog analogue test according to required, be provided with the slide bar of rotation connection, the rotation test to whole experimental aircraft model has been realized, observe the pneumatics of experimental aircraft model under the different angles of elevation, the holistic test comprehensiveness has been improved.
Description
Technical Field
The utility model relates to a wind-tunnel test field specifically is mini experience device of wind-tunnel dynamic test aircraft model.
Background
The wind tunnel experiment in the aspect of hydrodynamics refers to an aerodynamic experiment method for arranging an aircraft or other object model in a wind tunnel, researching gas flow and interaction between the gas flow and the model and knowing the aerodynamic characteristics of the actual aircraft or other objects. The prior art is comparatively rigid when carrying out analogue test to the aircraft model, can't come the aerodynamic nature under the different angles of elevation of experiment according to required angle of adjustment, and the aircraft model of test that can't be fine is controlled in the test, can't detect the internal test condition at any time, consequently need design one kind no matter daytime night can normally detect, control at any time the aircraft model in the test, can simulate out fog, the mini experience device of wind-tunnel dynamic test aircraft model of the condition of high-speed rotation at any time in the test.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a mini device of experiencing of wind-tunnel dynamic test aircraft model to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: mini experience device of wind-tunnel dynamic test aircraft model, including base and fixed plate, the top fixed mounting of base has the fan, the top of base and the one side fixed mounting who is located the fan have control panel, fixedly connected with fixed plate between control panel and the fan, the top of fixed plate and the one side fixedly connected with smoke flow appearance that is located the fan, control panel's top and the one side fixedly connected with wind-tunnel test cabin that is located smoke flow appearance, the top of base and the one side fixedly connected with amortization cabin that is located wind-tunnel test cabin of a fixedly connected with fixed block of surveying that is located control panel, the top of fixed block and the one side fixedly connected with amortization cabin that is located wind-.
Preferably, a rotating speed switch is fixedly mounted on one side of the fan.
Preferably, the top of the inside of the wind tunnel test cabin, which is located on the control panel, is rotatably connected with a sliding rod, the top of the sliding rod is fixedly connected with a placing table, and the top of the placing table is provided with a test airplane.
Preferably, the inner wall of the wind tunnel test chamber is fixedly provided with a spray head.
Preferably, an illuminating lamp is fixedly installed on the inner wall of the wind tunnel test cabin.
Preferably, the fan, the rotating speed switch, the spray head and the illuminating lamp are electrically connected with the control panel.
Preferably, the outer side of the wind tunnel test cabin is made of windproof transparent glass.
Compared with the prior art, the beneficial effects of the utility model are that: be provided with control panel and the experimental aircraft that has the operation panel, realized through controlling the platform, control experimental aircraft model, can observe the state of air current on aircraft model surface, be provided with the wind-tunnel test cabin of taking light and atomising head, the state of air flow through experimental aircraft model can all be observed no matter daytime night, can carry out fog analogue test according to required, be provided with the slide bar of rotation connection, the rotation test to whole experimental aircraft model has been realized, observe the pneumatics of experimental aircraft model under the different angles of elevation, the holistic test comprehensiveness has been improved.
Drawings
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a front view of the present invention;
fig. 3 is a side view of the structure of the present invention.
In the figure: 1. a base; 2. a fixing plate; 3. a fixed block; 4. a control panel; 5. a fan; 6. a smoke flow meter; 7. a wind tunnel test chamber; 8. a silencing cabin; 9. testing the airplane; 10. a slide bar; 11. a rotating speed switch.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1, fig. 2 and fig. 3, the present invention provides a technical solution: mini experience device of wind-tunnel dynamic test aircraft model, including base 1 and fixed plate 2, base 1's top fixed mounting has fan 5, base 1's top and the one side fixed mounting who is located fan 5 have control panel 4, fixedly connected with fixed plate 2 between control panel 4 and the fan 5, holistic stability has been realized, the top of fixed plate 2 and the one side fixedly connected with smoke flow appearance 6 that is located fan 5, control panel 4's top and the one side fixedly connected with wind-tunnel test cabin 7 that is located smoke flow appearance 6, normal running test has been realized, base 1's top and the one side fixedly connected with fixed block 3 that is located control panel 4, the top of fixed block 3 and the one side fixedly connected with amortization cabin 8 that is located wind-tunnel test cabin 7, a large amount of noise pollution that produces in the timely processing test has been realized.
Furthermore, a rotating speed switch 11 is fixedly installed on one side of the fan 5, so that the wind speed of the fan 5 can be adjusted as required.
Further, the inside of wind tunnel test cabin 7 and the top that is located control panel 4 rotate and be connected with slide bar 10, and the top fixedly connected with of slide bar 10 places the platform, and the top of placing the platform is installed test aircraft 9, has realized that can carry out the rotation test to the test aircraft 9 that tests.
Furthermore, the inner wall of the wind tunnel test chamber 7 is fixedly provided with a spray head, so that the fog can be simulated as required.
Furthermore, the inner wall of the wind tunnel test chamber 7 is fixedly provided with an illuminating lamp, so that the normal work can be realized no matter day or night.
Further, the fan 5, the rotating speed switch 11, the spray head and the illuminating lamp are electrically connected with the control panel 4, and the whole normal operation is realized.
Furthermore, the outer side of the wind tunnel test chamber 7 is made of windproof transparent glass, so that the inside of the wind tunnel test chamber can be observed at any time.
Specifically, use the utility model discloses the time: open control panel 4, place test aircraft 9 and fix at the platform of placing at slide bar 10 top, fan 5 operates, carry to wind-tunnel test cabin 7 inside through smoke flow instrument 6, thereby it is experimental, adjust the wind speed size according to required through speed switch 11 in the experiment, through atomising head simulation fog sight, internally mounted has the light, it can both observe at any time daytime at night to have made things convenient for the staff, adjust test aircraft 9 at any time through the operation panel on control panel 4, and control slide bar 10 rotates, realize the detection of test aircraft 9 in the pairing rotation, holistic experimental comprehensiveness has been improved, the noise pollution abatement who is brought that 8 ability maximize in amortization cabins that are equipped with brings the negative effect.
In the description of the present invention, it is to be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "one side", "top", "inner", "front", "center", "both ends", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
Furthermore, the terms "first", "second", "third", "fourth" are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated, whereby the features defined as "first", "second", "third", "fourth" may explicitly or implicitly include at least one such feature.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "disposed," "connected," "fixed," "screwed" and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, and may be connected through the inside of two elements or in an interaction relationship between two elements, unless otherwise specifically defined, and the specific meaning of the above terms in the present invention will be understood by those skilled in the art according to specific situations.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. Mini experience device of wind-tunnel dynamic test aircraft model, including base (1) and fixed plate (2), its characterized in that: the utility model discloses a wind tunnel test device, including base (1), the top fixed mounting of base (1) has fan (5), one side fixed mounting that the top of base (1) just is located fan (5) has control panel (4), fixedly connected with fixed plate (2) between control panel (4) and fan (5), the top of fixed plate (2) just is located one side fixedly connected with smoke flow appearance (6) of fan (5), the top of control panel (4) just is located one side fixedly connected with wind tunnel test cabin (7) of smoke flow appearance (6), the top of base (1) just is located one side fixedly connected with fixed block (3) of surveying of control panel (4), the top of fixed block (3) just is located one side fixedly connected with amortization cabin (8) of wind tunnel test cabin (7).
2. The wind tunnel dynamic test airplane model mini-experience device according to claim 1, characterized in that: and a rotating speed switch (11) is fixedly arranged on one side of the fan (5).
3. The wind tunnel dynamic test airplane model mini-experience device according to claim 1, characterized in that: the wind tunnel test cabin is characterized in that a sliding rod (10) is rotatably connected to the inside of the wind tunnel test cabin (7) and the top of the control panel (4), a placing table is fixedly connected to the top of the sliding rod (10), and a test airplane (9) is installed at the top of the placing table.
4. The wind tunnel dynamic test airplane model mini-experience device according to claim 2, characterized in that: and a spray head is fixedly arranged on the inner wall of the wind tunnel test chamber (7).
5. The wind tunnel dynamic test airplane model mini-experience device according to claim 4, characterized in that: and an illuminating lamp is fixedly arranged on the inner wall of the wind tunnel test cabin (7).
6. The wind tunnel dynamic test airplane model mini-experience device according to claim 5, characterized in that: the fan (5), the rotating speed switch (11), the spray head and the illuminating lamp are electrically connected with the control panel (4).
7. The wind tunnel dynamic test airplane model mini-experience device according to claim 1, characterized in that: the outer side of the wind tunnel test cabin (7) is made of windproof transparent glass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021966672.5U CN212674404U (en) | 2020-09-10 | 2020-09-10 | Mini experience device of wind tunnel dynamic test airplane model |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021966672.5U CN212674404U (en) | 2020-09-10 | 2020-09-10 | Mini experience device of wind tunnel dynamic test airplane model |
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| CN212674404U true CN212674404U (en) | 2021-03-09 |
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| CN202021966672.5U Active CN212674404U (en) | 2020-09-10 | 2020-09-10 | Mini experience device of wind tunnel dynamic test airplane model |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114383803A (en) * | 2022-03-22 | 2022-04-22 | 西南交通大学 | Wind tunnel test device for aerodynamic characteristics of pseudo-dynamic vehicle-bridge |
| CN114705390A (en) * | 2022-04-12 | 2022-07-05 | 中国空气动力研究与发展中心低速空气动力研究所 | Test device for simulating low-altitude wind shear in airplane lifting process |
| CN115959303A (en) * | 2023-03-16 | 2023-04-14 | 四川省天域航通科技有限公司 | Intelligent flight test method and application of large-scale fixed-wing freight unmanned aerial vehicle |
-
2020
- 2020-09-10 CN CN202021966672.5U patent/CN212674404U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114383803A (en) * | 2022-03-22 | 2022-04-22 | 西南交通大学 | Wind tunnel test device for aerodynamic characteristics of pseudo-dynamic vehicle-bridge |
| CN114383803B (en) * | 2022-03-22 | 2022-06-14 | 西南交通大学 | Wind tunnel test device for aerodynamic characteristics of pseudo-dynamic vehicle-bridge |
| CN114705390A (en) * | 2022-04-12 | 2022-07-05 | 中国空气动力研究与发展中心低速空气动力研究所 | Test device for simulating low-altitude wind shear in airplane lifting process |
| CN114705390B (en) * | 2022-04-12 | 2022-09-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Test device for simulating low-altitude wind shear in airplane lifting process |
| CN115959303A (en) * | 2023-03-16 | 2023-04-14 | 四川省天域航通科技有限公司 | Intelligent flight test method and application of large-scale fixed-wing freight unmanned aerial vehicle |
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